NBSIR 76-1050

Tornado- Borne Missile Speeds

Emil Simiu

Institute for Applied Technology

National Bureau of Standards

Washington, D. C. 20234

and

Martin Cordes

Institute for Basic Standards

National Bureau of Standards

Washington, D. C. 20234

April 1976

Final

Prepared for United States Nuclear Regulatory Commission

Washington, D. C. 20555

NBSIR 76-1050

TORNADO-BORNE MISSILE SPEEDS

Emil Simiu

Institute for Applied Technology

National Bureau of Standards

Washington, D. C. 20234

and

Martin Cordes

Institute for Basic Standards

National Bureau of Standards

Washington, D. C. 20234

April 1976

Final

Prepared for United States Nuclear Regulatory Commission

Washington, D. C. 20555

U.S. DEPARTMENT OF COMMERCE, Elliot L. Richardson. S^entmy

James A. Baker, III, Und»r S^crBfiy

Dr. Betsy Ancker-Johnson, Assistant Sacretary for Seianea and Taehnofogy

NATIONAL BUREAU OF STANDARDS, Emett Ambler, Acting Diraetor

Tornado - Borne Missile Speeds

Emil Simiu and Martin Cordes

• At the request of the United States Nuclear Regulatory Connnission (NRC) the National

Bureau of Standards (NBS) has carried out an independent investigation into the question

of tornado-borne missile speeds, with a view to assisting NRC in identifying pertinent

areas of uncertainty and in estimating credible tornado-borne missile speeds - within the

limitations inherent in the present state of the art. The investigation consists of two parts: (1) a study, covered in this report, in which a rational model for the missile

motion is proposed, and numerical experiments are carried out corresponding to various

assumptions on the initial conditions of the missile motion, the structure of the tornado

flow, and the aerodynamic properties of the missile; (2) a theoretical and experimental

study of tornado-borne missile aerodynamics, conducted by Colorado State University (CSU)

under contract with NBS, to be covered in a separate report by CSU. In the present

report, the factors affecting missile motion, and their influence upon such motion, are examined. Information is provided on a computer program developed for calculating missile

speeds. Maximum speeds for a number of specified potential tornado-borne missiles are

presented, corresponding to a set of assumptions believed by the writers to be reasonable

for design purposes. It is pointed out that higher speeds are conceivable if it is

assumed that certain circumstances, examined in the body of the report, will obtain. It is the judgment of the writers that the probabilities of occurrence of such higher speeds

for any given tornado strike are low. More than qualitative estimates of such probabilities

are, however, beyond the scope of this investigation.

KEY WORDS: Missiles; nuclear engineering; structural engineering; tornadoes; wind.

ACKNOWLEDGMENTS

The writers wish to acknowledge useful comments and suggestions by T.W. Reichard and

J.R. Shaver, of the Center for Building Technology, and J.F. Costello, of the Nuclear

Regulatory Commission.

iii

TABLE OF CONTENTS

Page

Abstract iii

Acknowledgements iii

List of Symbols vi

List of Figures - viii

List of Tables viii

1. Introduction 1

2. Model for the Tornado-Borne Missile Motion 2

3. Computer Program for Calculating Tornado-Borne 5 Missile Trajectories and Velocities

4. Numerical Computations 6

5. Sensitivity of Calculated Results to Changes in the 7 Assumed Initial Conditions or in the Assumed Tornado

Wind Speed Model

5.1 Changes in the Assumed Initial Position of the Missile 7 5.2 Changes in the Assumed Initial Velocity of the Missile 10

5.3 Changes in the Assumed Tornado Wind Speed Model 11

5.3.1 Tornado Described by Eqs. 5 through 9 with v„ = 0. 11

5.3.2 Tornado Vortex Model Based on Data Obtained During 11

the Dallas Tornado of April 2, 1957

6. Aerodynamic Forces . 17

7. Speeds of Selected Tornado-Borne Missiles 17

8. Conclusions 19

9. References 20

APPENDIX A - Equations of Motion. 21

APPENDIX B - Analytic Solution to the Equations of Motion for a Uniform Wind Field. 26

APPENDIX C - Documentation, and Sample Input and Output of Computer Program. 29

V
LIST OF SYMBOLS

effective area

projected areas

coefficient in Eq. 25

coefficient in Eq. 12

effective drag coefficient

drag coefficients corresponding to areas Aj^,A2,A2, respectively

lift coefficient

characteristic dimension of body

drag force

acceleration of gravity

vertical displacement

unit vectors

parameters of the tornado flow

mass of missile

radius (distance from vortex center)

value of r at which the horizontal velocity In the vortex flow

maximum

radius beyond which radial and vertical velocity components

vanish

Reynolds number

time

velocity

fluid velocity relative to the body

maximum horizontal missile speed

maximum horizontal wind velocity in vortex flow

missile velocity, with components Vw iv., »Vw M M M

X y z horizontal wind velocity in vortex flow

radial wind velocity in vortex flow

^m

translation velocity of tornado

wind velocity
= vertical wind velocity

Vq = tangential wind velocity in vortex flow

Vg = maximum tangential velocity m w = weight of missile

X = coordinate axis

y = coordinate axis

z = coordinate axis

a = angular displacement

V = kinematic viscosity

p = air density

vii
LIST OF FIGURES

Page

Figure 1 Bluff Bridge Deck Section 4

Figure 2 Notations 4

Figure 3 Variation of Maximum Horizontal Missile Speed 9 as a Function of C^k/m for Various Types of Tornadoes

Figure Al Notations 22

LIST OF TABLES

1. Values of V , V and R Used in Numerical Calculations 7 T m m

2. Maximum Horizontal Missile Speeds ^v'^^^ , (m/s) Corresponding to Various Initial 8 Positions

.

3. Maximum Horizontal Missile Speeds, vl\'**^, (m/s) Corresponding to Initial 8

Elevations z(0) = 10m, z(0) = 20m, zXO) ^ 40m (C^k/m = 0.001).

4. Maximum Horizontal Missile Speeds, v^**^* (m/s) Corresponding to Various 10

Initial Velocities.

5. Maximum Horizontal Missile Speeds, v?!^^, (m/s) Corresponding to Various H

Initial Positions (v^ =0).

6. Maximum Horizontal Missile Speeds, vTM^'^. (m/s) Corresponding to Various ^3

Parameter Values.

7. Comparison Between Calculated Speeds Based on Eqs. 13-24 and on 14

Eqs. 5-9.

8. Characteristics and Maximum Horizontal Speeds of Selected Missiles. 18

viii
1. INTRODUCTION

To ensure the safety of nuclear power plants in the event of a tornado strike it is

required that, in addition to the direct action of the wind and of the moving ambient pressure

field, the designer consider the impart of tornado-borne missiles, i.e., of objects

moving under the action of aerodynamic forces induced by the tornado wind. It is, therefore, necessary that estimates be made of the speeds attained by potential missiles under

tornado wind conditions specified for the design of nuclear power plants.

Several such estimates have been reported so far [1, 2, 3, 4, 5, 6, 7]. In certain

instances the differences between various estimates are very large; for example, the

predicted speeds of a utility pole [13-in (0.33 m) diameter and a 35-ft (10.7 m) length]

predicted by Refs. 5, 6, 1, 2, 4 and 3 are 16.5 m/s, 30.5 m/s, 41.2 m/s, 42.7 m/s, 52.2

m/s and 54.9 m/s, respectively. For any given missile, the kinetic energy associated

with translational motion is proportional to the square of the speed; in the case of the

utility pole, therefore, the ratio of the largest to the smallest of the kinetic energy

estimates of Ref. 1 through Ref. 6 is greater than 10. For other missiles, the ratio

varies from almost 2 in the case of a 1-in (2.54 cm) diameter steel rod to over 5 in the case of a 4000 lb (18,000N) standard automobile.

In most cases, such large discrepancies are the consequence of differences between

basic assumptions used in the various estimation procedures. These assumptions include:

- the initial conditions of the problem, i.e., the initial position of the object

with respect to the ground and to the tornado center, and the initial velocity

of the object.

the detailed features of the wind flow field.

- the aerodynamic characteristics of the object (which, in most cases of practical

interest, is a bluff body)

.

Differences between the various sets of basic assumptions used in estimating tornadoborne missile velocities may be ascribed, in part, to the probabilistic nature of the

problem. Indeed, for any given tornado wind field, the initial conditions constitute a set or random variables with a very large number of possible values, the choice of which

is not unique. More importantly, however, such differences are a consequence of serious

uncertainties regarding both the structure of the tornado flow and the aerodynamic behavior

of the potential missile.

1
At the request of the United States Nuclear Regulatory Commission (NRC) , the National

Bureau of Standards has carried out an independent Investigation into the question of

tornado-borne missile speeds, with a view to assisting NRC in identifying pertinent areas

of uncertainty and in estimating credible tornado-borne missile speeds —within the limitations

inherent in the current state of the art. The objectives of the investigation were defined as follows:

1. To select a rational model for the tornado-borne missile motion.

2. To develop a computer program based on this model, capable of computing missile

trajectories and velocities for any specified initial conditions, tornado wind

speed model, and assumptions regarding the drag force acting on the missile.

3. To calculate, for a specified set of initial conditions and for a specified

wind speed model, the trajectories and velocities corresponding to a number of

specified potential missiles.

4. To determine, in a number of representative cases, the sensitivity of the

calculated results to changes in the assumed initial conditions or in the

assumed tornado wind speed model.

5. To obtain and interpret information, based on wind tunnel tests, regarding the

aerodynamic behavior of various potential missiles, i.e., drag coefficients for

various missile motions, including motion in the tumbling mode.

6. From the results of items 3, 4 and 5, suggest credible speeds of selected

potential tornado-borne missiles, compatible with the current state of the art

in nuclear power plant design.

2. MODEL FOR THE TORNADO-BORNE MISSILE MOTION

The motion of an object may be described in general by solving a system consisting

of three equations of balance of momenta and three equations of balance of moments of

momenta. In the case of a bluff body, one major difficulty in writing these six equations

is that the aerodynamic forcing functions are not known.

It is possible to measure in the wind tunnel aerodynamic forces and moments acting

on a bluff body under static conditions for a sufficient number of positions of the body

with respect to the mean direction of the flow. On the basis of such measurements, the

dependence of the forces and moments on position, and corresponding aerodynamic derivatives,

can be obtained. Aerodynamic forces and moments can then be calculated following the

well-known pattern used in airfoil theory; for example, if an airfoil has a time-dependent

vertical motion h(t) in a uniform flow with velocity U, and if the angle of attack is a = const, the lift coefficient is

r - '^^L , _^ 1 dh,

^L - d^ U dF) (1)

This procedure for calculating aerodynamic forces and moments is valid if the quasisteady assumption [Ref. 8, p. 192] is acceptable and if the body concerned behaves
aerodynamically like an airfoil - i.e., if the body is streamlined and if no flow separation

occurs. However, in the case of unconstrained bluff bodies moving in a wind flow the

validity of such a procedure remains to be demonstrated.

In the absence of a satisfactory model for the aerodynamic description of the

missile as a rigid (six-degrees-of -freedom) body, it is customary to resort to the alternative

of describing the missile as a material point acted upon by a drag force

D = 1/2 p C^A r - I (v^ - •

where p = air density, v = wind velocity, v = missile velocity, A is a suitably chosen w . M

area and C^^ is the corresponding drag coefficient.

This model is reasonable if, during its motion, the missile either (a) maintains a constant or almost constant attitude with respect to the relative velocity vector vw

v„» or (b) has a tumbling motion such that, with no significant errors, some mean value

M

of the quantity C^^A can be used in the expression for the drag D. The assumption of a constant body attitude with respect to the flow would be credible if the aerodynamic

force were applied at all times exactly at the center of mass of the body—which is

highly unlikely in the case of a bluff body in a tornado flow—, or if the body rotation

induced by a non-zero aerodynamic moment with respect to the center of mass were inhibited

by aerodynamic damping forces intrinsic in the body-fluid system. The question thus

arises as to whether such stabilizing forces may be expected to be present.

It is of interest at this point to mention certain experimental results—obtained in

studies of bridge deck aerodynamic stability—which provide useful insights into the

question at hand. Consider a body restrained by four springs of equal stiffness, immersed

in a horizontal flow (Fig. 1) , and subjected to an impulse which produces angular oscillations

6(t) about the position of equilibrium [9]. In the case of an airfoil with a sufficiently

small angle of attack so that flow separation does not occur, the aerodynamic damping,

which is proportional to the quantity denoted by H* in Ref . 9, is positive. This implies

that the flow will contribute , along with the viscous damping inherent in the springs,

to the damping out of the oscillations. On the other hand, for bluff bodies, at high

velocities of the flow and for vanishing values of the spring stiffness, the aerodynamic

damping is negative in the large majority of the cases tested [9] These results suggest that, in general, no stabilizing effect by the flow can be

expected to inhibit the tumbling of bluff bodies. The assumption that potential tornadoborne missiles will tumble during their motion appears therefore to be reasonable. It will be this assumption that will fee used in this work.

3

Assuming that Eq. 2 is valid and that the average lift force vanishes under tumbling

conditions, the motion of the missile viewed as a one-degree-of-freedom system is governed

by the relation:

'^^M , ,„ C A

I - - I - - - (3) -r— = - 1/2 p _D_ V - V (v^ - V ) - gk

dt ' M w ' M w

m

where g = acceleration of gravity, k = unit vector along the vertical axis and m = mass of

missile.

It follows from Eq. 3 that for a given flow field and initial conditions, the motion

depends only upon the value of the parameter C A/m. Throughout this work, the area. A, will

2 be expressed in m and the mass, m, in kg. To transform the parameter C A/w, where A is

2 expressed in ft and the weight in lb, into the parameter C A/ m, where A is expressed in

2 m and the mass, m, in kg, the following relations are used:

-2- = 1 If- = .205 f- ^^^^ w lb m kg

^

C^A 2 C^A ^2

=l2_ -> = 4.902 1^- (4b) m kg w lb

3. COMPUTER PROGRAM FOR CALCULATING

TORNADO-BORNE MISSILE TRAJECTORIES AND

VELOCITIES

To calculate and plot trajectories and velocities of tornado-borne missiles, a computer program was developed in which the assumed models for the tornado wind field and

the drag coefficients are specified by specialized subroutines (details of such models

are given in subsequent sections)

.

In Eq. 3 the components of the missile velocity v,, and of the wind velocity v must _M w

be referred to an absolute frame. The wind velocity v^ is usually specified as a sum of

two parts. The first part represents the wind velocity of a stationary tornado vortex

and is referred to a cylindrical system of coordinates. The second part represents the

translation velocity of the tornado vortex—or, equivalently , of the cylindrical system

of coordinates —with respect to an absolute frame of reference. The transformations

required to represent v in an absolute frame are derived in Appendix A and are incorporated w

in the computer program. Documentation on the computer program and a sample input and

output are given in Appendix C. The program, which is written in ANSI Fortran language,

may be obtained on tape from the National Technical Information Service, Springfield,

Virginia 22151.

For the particular case of a parallel flow, an analytical solution to the problem of

the missile trajectory can be easily obtained. This solution, which can be found in

Appendix B, has been used to test the program, in which the subroutine describing the

wind field was modified to represent a parallel flow.
4. NUMERICAL COMPUTATIONS

It was previously noted that, for a given flow field and for given initial conditions,

the missile motion depends only upon the value of the parameter C^A/m. In this section,

numerical results will be presented which show the effect of this parameter on the maximum

horizontal missile speed. The calculations are based on the following assumptions:

1. The parameter C^A/m is constant during the missile flight.

2. The tornado wind field may be represented by a vortex translating with a

2 uniform velocity v^ along an axis denoted by Ox (Fig. 2). Let v„, v„ , v and v = (v„

2 R 9 z rot R + V ) denote the radial, tangential, vertical and horizontal velocity in the vortex

6 flow, respectively. It is assumed that

^rot =|-v 0<r<R (5) R m — — ra m

R rot = — V R<r<<» (6) r m m — —

where v is the maximum horizontal velocity in the vortex flow, r is the radius (distance m

from the vortex center) and R is the value of r at which this velocity is attained. m

Eqs. 5 and 6 are similar to descriptions of the flow proposed in Ref . 10 (p. 135).

Furthermore, it is assumed that = 1/2 v^ and v^ = 0.67 v^ , i.e., (see Fig. 2).

1 V = — V

R rot (7)

2

^ ''e /"s-'^rot (8)

V = V (9)

z 3/^

The type of model just described is referred to as the Rankine vortex and appears to be a reasonable representation of tornado flows. Estimates based on field observations

suggest that it is reasonable to assume—as is done in this model—that R is independent

of height [Ref. 10, p. 131].

6
The following values for the tornado wind field parameters were used in the calculations:

Table 1 - Values of v„, v and R Used in Numerical Calculations

T m m

v_ V V = R

i torn m 1 TH Tornado m/s* mph m/s* mph m/ s* mph m* ft

Type

1 31 70 130 290 161 360 46 150

2 27 60 107 240 134 300 46 150

3 22 50 85 190 107 240 46 150

4 31 70 146 325 177 395 46 150

5 27 60 120 288 147 348 46 150

6 22 50 95 213 117 263 46 150

* Approximately

The values given in Table 1 for tornado types 1, 2, 3 are suggested in Ref. 11 as providing

an acceptably low level of failure if used in the design of nuclear power plants. The

values for tornado type 4, 5 and 6 were included for the purpose of studying the effect

upon missile velocity of relatively small increments in the value of v^.

3. The assumed initial conditions are: x(0) = R , y(0) = 0, z(0) ,= 40m, v„ (0) = 0, m Mx

v., (0) = 0, v., (0) = 0 at time t = 0, where x, y, z are the coordinates of the missile

My Mz

(i.e., of its center of mass) and v., , v^, , v,, are the missile velocity components alone

Mx My Mz J r b the X, y, z axes (Fig. 2), Also, at time t = 0 the center of the tornado vortex coincides

with the origin 0 of the coordinate axes. The effect of assuming initial conditions different

from those indicated is examined in the next section of this report.

The dependence upon the parameter C^A/m of the maximum horizontal missile speed calculated

in accordance with assumptions 1 through 3 is represented in Fig. 3 for tornado types 1 through 6 as defined in Table 1. In Fig. 3 v = v^ + v (Table 1). torn i m

5. SENSITIVITY OF CALCULATED RESULTS

TO CHANGES IN THE ASSUMED INITIAL

CONDITIONS OR IN THE ASSUMED TORNADO

WIND SPEED MODEL

5.1 Changes in the Assumed Initial Position of the Missile . For flows with vmm= 146 m/s, R = 46 m, and v„ = 31 m/s, the maximum horizontal

1 speeds of missiles with C^A/m = 0.001 and C^A/m = 0.01 were calculated using the initial

positions shown in Table 2. Except for the initial positions, the results of Table 2 are based on the assumptions described in the preceding section. It is seen from Table 2 that

7
Table 2 - Maximum Horizontal Missile Speeds, v^^^ , (m/s)

Corresponding to Various Initial Positions

Initial Position Cj^A/m

(1) (2) (3) (4) (5) (6)

x(0) y(0) (J . UUl U . U.L (meters)

(a) o- 46 0 10 65

(b) G- 23 0 18 93

(c) 69 0 9 48

(d) o- -46 0 18 82

(e) 0 46 16 68

(f) 0 23 20 84

(g) 0 -23 35 50

(h) 0 -46 54 70

1. Arrows in column (2) represent direction of translation velocity

2. Assumed elevation of missile at time t = 0: z(0) = 40m in all cases.

Table 3 - Maximum Horizontal Missile Speeds, (m/s) Corresponding to Initial Elevations 2(0) = 10m . z(0) = 20m and z(0) = 40m (C A/m = 0.001 )

Initial Position z (0)

(1) (2) (3) (4) (5) (6) (7)

^(0) y(0) 10m 20m 40m

(meters)

(a) o -> 46 0 6 7 10

(b) G -> 23 0 2 8 18

(c) -> 69 0 9 9 9

(d) -> -46 0 14 16 18

(e) 0

-» 0 46 3 9 16

(f) -» 0 23 12 16 20

(g) Q

-> 0 -23 19 29 35

(h) Q

-> 0 -46 33 42 54

8
a. Q. E E

in o

0) to

ro to

II II i| > > I II I « 

^ —

CVJ o

<J>

11 <oo1

(0 >v \CM H- E 00OJ

II rO E II < u> \E o f Q. a. a. a. E E E E

CO

O ro o

rC rO CM CM

S/UJ m/s

ME

m/s

1^

ro o

II II II II co

UJO orn UJO >

>" 1 1 > >

ic * m CVl (0 ro

UJ

a.o « a 2 <^

SO)

CO <+-4 u O eo fl N O

•H •H

O

M

U

O o CO c 0) 3 a. 1 H

ca •H CO CO 3

cd o

•rH T3

(U

O OJ >

(X c CO

u CD o 0 0) •H (U 0

4J .H

a Cfl •r-( a Cfl •H CO c

f-J CO <C

ta •H QO > 2 H ^3

bO •H o O00 O1^ oin o o

ro

O

OJ o

(s/uu)

XDUJ'9
the initial position used in the calculations of the preceding section, (position (a) of

Table 2) does not result in the largest possible maximum horizontal missile speeds.

It is also noted that the initial positions to which there correspond the largest possible

missile speeds depend upon the value of C^A/m. For example, for C^A/m = 0.01, that initial

position is (b )

; for C^k/m = 0.001, it is (h) [see Table 2].

As indicated in Note 2 of Table 2, the initial elevation assumed in the calculations

was z(0) = 40m. If the weight of the missile is smaller than the upward drag induced

by the vertical wind velocity component, then the calculated missile velocities at time t are independent of 2(0) . (This is the case because, in the assumed tornado model, the

flow field is invariant with z) . However, if the missile weight exceeds the upward drag,

i.e., if the missile moves downward, —as in the case of column (5) of Table 2 — the

interval between time t = 0 and the time at which the missile hits the ground decreases as

z(0) decreases. Therefore, the maximum missile speed may decrease if lower values of the

initial elevation z(0) are assumed. Table 3 lists speeds calculated using the assumptions

z(0) = 10m and z(0) = 20m, all other values of the various parameters being the same as

for column (5) of Table 2. For comparison the calculated speeds in column (5) of Table 2 were also included in Table 3. Missile speeds were also calculated corresponding to various initial elevations

0 < z (0) < 10m. It is of interest to note that the maximum horizontal speed of a missile

with CjjA/m = 0.001 starting the motion from position (h) is relatively high even for low

values of the initial elevation z(0). For example, for z(0) = 3m and z(0) = 5m, the maximum

missile speeds are 23 m/s and 27 m/s, respectively.

Calculations were also carried out for the horizontal distances traveled by the

missiles. For example, for C^A/M = 0.001 and the initial position (h) , the horizontal

distances corresponding to z(0) = 3m, 5m, 10m, 20m, and 40m are, approximately, 20m, 30m,

50m, 90m and 160m, respectively.

5.2 Changes in the Assumed Initial Velocity of the Missile . The results given in the preceding sections are based on the assumption that the

initial velocity of the missiles is zero. If the missile is injected in the flow, for

example by an explosion, this assumption is no longer valid. However, all other conditions

being equal, a non-zero intial velocity does not necessarily result in a maximum missile

velocity higher than that corresponding to zero initial velocity. This is illustrated

in Table 4, in which type 1 tornado (see Table 1), and the conditions ^^^^^(0) ^ 0,

Vw (0) = 0, v., (0) = 0 were assumed. My Mz Table 4 - Maximum Horizontal Missile Speeds, vTM^^, (m/s) Corresponding to Various Initial Velocities

C^k/m = 0.001 C^A/m =0.01

(2) (3) (4) (5) (7) (8) (9) (10)

x(0) y(0) (meters /second)

(meters) 0 10 20 0 10 20

(a) 46 0 8 9 20 62 58 53

(g) 0 -23 35 45 35 63 59 59

10
5.3 Changes in the Assumed Tornado Wind Speed Model . 5.3.1 Tornado Described by Eqs. 5 through 9 with v = 0.

Table 5 lists maximum horizontal missile speeds for the same parameter values and

initial conditions as those used in Table 2, except that the translation velocity of the

tornado vortex is zero, rather than 31 m/s. It is seen by comparing Tables 2 and 5 that

the calculated speeds are, on the average, higher in the case v^ = 31 m/s, although for some initial positions the reverse is true.

Table 5 - Maximum Horizontal Missile Speeds, v^

Corresponding to Various Initial Positions (v = 0)

Initial Position Cj^A/m

(1) (2) x(0) y(0) (2) (3)

(meters) 0.001 0.01

(a) o 46 0 30 65

(b) 23 0 7 61

(c) 8- 69 0 19 60

(d) -46 0 30 65

(e) 6 0 46 30 65

(f) 0 23 8 61

(g) 0 -23 8 61

(h) 0 -46 30 65

5.3.2 Tornado Vortex Models Based on Data Obtained During the Dallas Tornado of

April 2. 1957 [13]. In this family of models, the velocities in the tornado vortex depend upon the quantities

= radius of maximum tangential velocity at elevation z = 0, Vg^ = maximum tangential

velocity and R*(z) = radius beyond which the radial and vertical velocity components

vanish. In addition, the flow depends on three parameters k^^, k^, k^, as will be shown

subsequently. The radius of maximum tangential velocity at elevation z is denoted by

R (z) and is assumed to be m

R (z) = R + k, z 0 < z < 60m (10) m m 1 ^ '

R (z) = R + 60 k, z > 60m (11) m m 1 —

It is seen that the parameter k^^ is a measure of the extent to which the tornado

vortex deviates from a cylindrical shape. If k^^ = 0 the radius of maximum tangential

velocity is invariant with height, as in the model described by Eqs. 5 through 9. An

assumption commonly employed in tornado-borne missile speed investigations is k^ = 0.45

[see, for example, Refs. 3 and 12], It is further assumed [3, 12]:

11
R* (z) = CR^ (z) (12)

where C Is a coefficient which depends upon Vg^. In this work, it was assumed C = 2.35

for V. = 130 m/s, C = 2.10 for v„ = 107 m/s and C = 1.80 for v„ = 85 m/s. These values

om t)m bm are similar to those used in Ref. 3. Let r denote the distance to the center of the tornado vortex. The components

of the velocity in the tornado vortex are assumed to be

0 < z < 60m

V - k R* (z) - r „^ , , R " 2 R* - R (2) r r < R* (2) (13) m

" 0 r > R*(z) (14;,

\ = r-fir ^m • ^

< ^^^^ m — m

R

V. r > R (z) (16)

r 9m m \ ' S R* [I] : R (z) ^ r r<K*(z) (17)

«= 0 r > R* (z) (18)

60 m < z < 240m

, R* (z) - r 240 - z , ^ /-.ox ^ R* (z) - R^ (z) ^ ' ^

^*

= 0 r > R* (z) (20)

v_ =

Tl^ ^em ^ (21)

\ (z)

^m > \ (22)

-z " - lfo> (^3 R* (z! : R (z) ^° r> ^ < ^* (23)

= 0 r > R* (z) (24)

12
Table 6 - Maximum Horizontal Missile Speeds v"^"^. (m/s) Corresponding to Various

Parameter Values

Case ^em ^2 "3 Cj^A/m

max \

(m/s) (m/s) m-^/kg (m/s)

1 85 22 .45 1 1 0.025 90*

2 85 22 .45 1 0 0.025 83*

3 85 22 0 1 0 0.025 77

4 85 22 0 1 1 0.025 79

5 130 31 .45 1 1 0.025 90*

6 130 31 .45 1 0 0.025 126*

7 130 31 0 1 0 0.025 80*

8 130 31 0 1 1 0.025 75*

9 130 31 .45 1 1 0.01 91*

10 130 31 .45 1 0 0.01 87

11 130 31 .25 1 0 0.01 73

12 130 31 0 1 1 0.01 60

13 130 31 0 1 0 0.01 60

14 130 31 .45 0 1 0.025 60

15 130 31 .45 0 1 0.01 36

* Calculated speeds are higher at z > 60m.

13
The most commonly used value of the parameter is unity (see, for example, Ref. 3 and

12). However, it is by no means certain that Eqs. 13 and 19 with "'" ^ satisfactory

model of the radial velocity v^^. Indeed, according to Ref. 10 (p. 135), v^^ is negligible

throughout the tornado flow except in the vicinity of r = R^ (z) . It is, therefore, of

interest to examine the influence upon the calculated missile speeds of the assumption

V =0. This can be done by assuming k„ = 0 in Eqs. 13 and 19. R ^ Similarly, while it is commonly assumed = 1, it is of interest to examine the

case in which the value of the vertical velocity component v^ is smaller than that given

by Eqs. 17 and 23 with = 1. This can be done, for example, by assuming k^ = 0. Calculations of missile trajectories and speeds based on the assumption that the

tornado vortex is described by Eqs. 13 through 24 were carried out for the 15 cases

listed in Table 6. In all cases of Table 6 it was assumed x(0) = R^^, = 46m, y(0) = 0,

z(0) = 0. Table 6 only includes the maximum calculated horizontal missile speeds v'"^^

at elevations z _< 60 m. A discussion will now be presented of the results of Table 6. The cases corresponding

to the set of parameters k^ = 0.45, k^ = 1, k^ = 1 which, as previously Indicated, are most commonly assumed in missile speed calculations, will be examined first. It is

noted that the missile speeds for cases 1, 5 and 9 of Table 6 are higher than the corresponding

speeds of Fig. 3, as shown in Table 7.

Table 7 - Comparison between Calculated Speeds Based on Eqs. 13 through 24 and on Eqs . 5 through 9

Table 6 Figure 3

m

Case max

(m/s)

Tnrnado

Type

max

(m/s)

0.025 1 90 3* 57

0,025 5 90 1* 81

0.01 9 91 1* 63

* See Table 1

This can be explained as follows. Assume that ~ '^j ~ ^ ^'^'^ that the missile starts

from an initial position x(0) = R . As the missile gains momentum, it tends to fly in a m

straight line along the direction of the tangential velocity, i.e., at larger distances

from the center of the vortex. In the case of a tornado with a radius of maximum tangential

speed that is constant with height, as the missile moves away from the intial position, it

will be subjected to winds of lower intensity and its speed will increase more slowly.

On the other hand, if the radius of maximum tangential speed increases with height, and if

the elevation of the missile increases under the action of vertical wind speed components

larger than the missile weight, then as the missile moves away from the center and up it

continues to fly in zones of maximum winds and thus continues to gain momentum at a fast

14
rate. This mechanism is modified only slightly in most, although not in all cases, if non-zero radial and translation velocities are present. The explanation just advanced

is confirmed by comparing cases 4 to 1, 8 to 5, and 12 to 9. In cases 4, 8 and 12, =

0, i.e., the radius of maximum tangential velocity is constant, and the missile speeds

are lower than in cases 1, 5, 9, in which that radius increases with height. A similar

conclusion is reached by comparing cases 3 to 2, 7 to 6, 11 and 13 to 10.

The parameter k^, which controls the magnitude of the vertical wind velocity component,

does not appear to affect the missile speeds in a uniform fashion, i.e., to the value

= 0 there correspond in certain cases lower values of the missile speed than to the

value k^ = 1 (e.g., case 2 vs. case 1); in other cases, the reverse is true (e.g., case

6 vs . case 5)

.

Some meteorologists have expressed the view that the radial velocity component v

R

is smaller over most of the tornado field than that described by either Eq. 7 or Eqs . 13

and 19 with k^ = 1[10] . It is therefore of interest to examine the case = 0. It is seen, by comparing in Table 6 cases 14 and 15 with cases 5 and 9, respectively, that the

assumption k^ = 0 results in considerably lower missile speeds than the assumption k^ =

1. This is the case because, if k = 0, (i.e., if v = 0) , the missile is ejected

Z K

(i.e., it flies at larger distances from the center of the vortex and therefore, in a region of lower speeds) sooner than if = 1, (i.e., than if a radial velocity is

present that resists the tendency of the missile to fly away from the center) . This

reasoning is valid for the assumed initial condition x(0) = R , y(0)= 0. it is conceivable m

however, that initial conditions exist which might result in higher missile speeds for

k^ = 0 than for k^ = 1.

6. AERODYNAMIC FORCES

In this work it was assumed that the aerodynamic force acting upon a missile is

D = 1/2 p C^A I V - v„ I (v - O (24) D ' w M ' w M

where p = air density, v^ = wind velocity, v^^ = missile velocity and C^A is a suitably

chosen quantity with the dimensions of an area. As indicated in Section 2, Eq. 2 may be

assumed to be valid under random tumbling conditions, i.e., if the motion is such that

the body "presents all possible aspects to the flow, . . . the orientation of the surface

elements with respect to the flow sweeps through all the possible angles" (Ref . 14) and,

moreover, the angular speed of the tumbling body is sufficiently large. In this connection

it may be argued that, instantaneously, lift forces do exist, and that the momentum they

impart to the missile may not be negligible if the rotational motion of the missile is

relatively slow. The acceleration of the missile would then no longer be parallel, at every instant, to the vector v - v and the missile trajectory would deviate from that w M

predicted by using the aerodynamic model implicit in Eq. 2. It is believed, however,

that the effect of such deviations on the maximum speed of the tornado-borne missile is

15
comparable to the effect of changes in the initial conditions of the problem such afe were

stud .led i.n Section 5. For the purposes of this report, the existence of lift forces which

are not taken into account in the calculations is believed not to invalidate the aerodynamic

model used herein.

The value C^^A that corresponds to tumbling conditions can, in principle, be determined

experimentally. Unfortunately, little information on this topic appears to be presently

available. Ref . 14 examines tumbling motions for supersonic wind conditions, while Ref

.

15 contains information on tumbling under flow conditions corresponding to Mach numbers

0.5 to 3.5. Hoerner extrapolated the data of Ref. 15 to lower subsonic speeds (Ref. 16,

p. 14-16, Fig. 7); according to this extrapolation, for a randomly tumbling cube the

quantity C^^A equals, approximately, the average of the products of the projected areas corresponding to "all positions statistically possible" by the respective static drag

coefficients (Ref. 16, p. 14-16 and P. 13-17). An investigation into this question is

currently carried out, within the framework of this project, by Colorado State University

(CSU) . The theoretical and experimental results of this investigation will be reported

in a separate document by CSU.

In the absence of more experimental information, it appears reasonable to assume

that the effective product Cj^A is given by the expression

V = \h ^ S3^3> (25)

in which Cjj A^ (i = 1, 2, 3) are products of the projected areas corresponding to the cases in which the principal axes of the body are parallel to the vector v - v.,, by w M

the respective static drag coefficients. In Eq. 25, c is a coefficient assumed to be

0.50 for planks, rods, pipe and poles and 0.33 for the automobile.

An upper bound for the quantity Cj^A is believed to be

(C^A) = (26)

in which C^^ A^ is the largest of the quantities C^^ A^ (i = 1 , 2 , 3) . The Reynolds number is defined as

^

Re =^V

where V = fluid velocity relative to the body, d = characteristic dimension of the body

(in the case of a cylinder, d = diameter) and v = kinematic viscosity (v = 1.5 x 10~^

m/s for air). For a circular cylinder Re - .67 x 10^ Vd, where V and d are expressed in

m/s and m, respectively. For Re > 4 x 10^, i.e., the Reynolds number is in the supercritical

range and it may therefore be assumed, conservatively, Cj^ = 0.7 (see Ref. 8, p. 67). In the case of the 1 inch (2.54 cm) rod, it may be assumed tftat Re is in the subcritical

range even for velocities V of the order of 100 m/s and, therefore, that C = 1.2 (Ref. 8).

°1

16
7. SPEEDS OF SELECTED POTENTIAL TORNADO-BORNE MISSILES

In this section calculated speeds of selected potential tornado-borne missiles will

be given, based on the following assumptions:

(1) The model of the tornado vortex consisting of Eqs. 5 through 9 is valid, with

the parameter values corresponding to cases 1, 2 and 3 of Table 1.

(2) The initial conditions are x(0) = R , y(0) = 0, z(0) = 40m (for comments on m

the initial condition z(0) = 40m, see p. lo of this report); v^(0) =

'^My^^^ " ^Mz^^^

= 0. Assumptions (1) and (2) just described were used in calculating the values on

curves 1, 2 and 3 of Fig. 3.

(3) The effective product Cj^A is given by Eq. 25.

The results of the calculations based on these assumptions are shown in Table 8. The missile speeds of Table 8 are based on a set of assumptions which, while reasonable,

might in certain cases not correctly reflect the actual physical phenomenon. It follows

from Sections 5 and 6 that the order of magnitude of uncertainties in the estimates

of maximum missile speeds can in certain cases be as high as 50% or even more. Whether

or not actual missile speeds will be higher than those listed in Table 8 depends in

large measure on the extent to which the tornado flow model consisting of Eqs. 5 through

9 (the so-called Rankine vortex) is realistic. In particular, if, as suggested in Ref

.

10, the radial and vertical velocity components in a tornado are actually lower than

those given by this model, it could be expected—all other conditions being equal

that the predictions of Table 8 are conservative. If, on the other hand, the actual

tornado flow is more closely represented by Eqs. 13 through 24 with certain unfavorable

values of the parameters included in these equations, then higher missile speeds than

those of Table 8 may occur, as shown in Tables 6 and 7. The speeds of Table 8 may also be exceeded if unfavorable initial conditions obtain.

The uncertainties pertaining to the tornado flow modeling are due to the lack of reliable

information; on the other hand, those pertaining to the initial conditions are a consequence

of the probabilistic nature of the problem. Probabilities of occurrence may be assigned

to each set of initial conditions. The probability that (a) the wind speed will reach

the intensity levels of Table 1, (b) that a missile starts from a highly unfavorable

set of initial conditions and (c) that it will hit a certain installation with a speed V

H can be. expected to be negligibly low. Such probabilities can in principle be evaluated

using, for example, procedures similar to those outlined in Ref. 18. Attempts to calculate

such probabilities are beyond the scope of this work.

17
Qau tn w m c \ E a

C OJ U-J B ^ B B «-i , E u-l u-l E

u a. o <T vD ro o >> 00 o f—i CM GO 00 CNJ CN H H rH 1—

I

f—

(

<r CO

^—^—

'—

—^

< O 05 to tn CO U) 0) 10 —

a. D. B Cl E a E

1 as u-t B 4-4 6 S u-l u-l U4 > E ft- o 00 o .—1 o CO CNI 00 o CN CN CO uo a^ CM O >^ CM 1-H -J" m .-H .—1 —

—^

O Ul (/I (A yi U) \ m

'—

n] fp £

cx

u-l B f

r» E U-( E rP E o.

u-l E C 0) eg r—

(

m o M a CM ON Ov in 00 In in o >^ 00 .—1 m i-H H H

CM o O CO o o (M CO in CO

(N O o O o C

a C o o o o C

<; O o o o

QU

oO

O

O

O

o

CM

CO

•J3 CO

in • o -*

CN >, rH (S vO

n) 00 4-1 00 >^ CM n 00 o • Id CO

CN H u o to

-3-

4J lO

J=

-a 00 vO

iH v£> •H CO ^ H

CJN lb we CM O <n O 4J

4J a\ o iH o (0 vO m m CN 00 o 4-1 • cd O CM ca Oi

CO 4-1 CN ^ -*

00

00 •

00

CMO

X0 'b

CM \0

C7\ vCi O •

• CO

tH 60 wTJ C X

«) rH a

r ^-^ 00 in - vo

CM m rH \0 rH • o

- CO X

• a

CO O

X

/-^ X §4-10

•H C3 m

TJ (U CM ^ rH O

a 60 X

<d C

•ri <u a ^ ^

T3 rH O a

00

CO vO

: - -3- • m m CO o

CO o

a 4J m

(d 60 • •ri (3 -a- ^ rH X V—

: a m - CM m CO

CM o

c

01o

o

o o. m th

014 VO

O

ao

•aO T>

(/} O

U lU

rH rH rH

OJ v ID rH rH rH

Si ja

ns to Id H H

OJ U (V

01 (U 01

(0

1

01 (fl

1 2' a a. a. e E a c O o vO o -3- CO CM

m

E s "a

rH -3- vO CO O rH rH rH

II II II

18
The uncertainties regarding the actual aerodynamic drag coefficients constitute

another source of error. It is noted that the curves in Fig. 3 are S-shaped. Large

errors in the assumed value of the quantity C^^A may therefore in certain cases result in

considerable changes of the estimated value of VTMt^ For example, if, for a 12 in Sch.

2 40 pipe (entry 6 in Table 8) it was assumed C^A/m = 0.0066 kg/m instead of C^A/m = 0.0033

kg/m^, it follows from Fig. 3 that V^^^ = 40 m/s, rather than VTM^^ = 7 m/s, as in Table

8. It is interesting to note, on the other hand, that as long as a change in the assumed

value of Cj^A/m does not displace the point from the upper or from the lower branch of an S-shaped curve, the sensitivity of V^^^ to even considerable changes in the value of C A/m

is fairly small. For example, if for the 6 in Sch. 40 pipe (entry 2 in Table 8) it is assumed

that C A/m = 0.0086, then, for a tornado type 1, VTM^^ = 61 m/s (see Fig. 3), whereas to ax

the assumption C^A/m = 0.0043 there corresponds V? ^= 52 m/s, i.e., to an error of 100% in

D H the value of C A/m there corresponds an error of only 17% in the estimated value of V D n Finally, it must be noted that the actual missiles may have properties that are more unfavorable than those listed in Table 8; for example, the case is mentioned in

Ref . 19 of a beam attached, during its flight, to a portion of a carport roof which

considerably increased the surface area of the missile and, therefore, the parameter

CjjA/m.

8. CONCLUSIONS

In the preceding section calculated maximum speeds of tornado-borne missiles are

given in Table 8, based on a set of assumptions believed to be reasonable. However, in

assessing these speeds, it must be recognized that:

1. The problem of determining tornado-borne missile speeds has a probabilistic

character. As shown in the body of the report, unfavorable initial conditions may

obtain—to which there correspond relatively low probabilities of occurrence—for

which the maximum missile speeds would be higher than in Table 8. The estimation of

such probabilities is beyond the scope of the investigation covered by this report.

2. Estimates of tornado-borne missile speeds are also affected by significant

uncertainties with regard to: (a) the detailed structure of the tornado flow and

(b) to the aeordynamic behavior of the missile. Under certain assumptions regarding

one or both of these factors, calculated missile speeds can be higher than those

of Table 8. However, it is believed that the assumption used to derive the values

of Table 8 are conservative. In particular, it is believed that the actual vertical

wind speeds are lower than indicated by Eq. 9, so that the relatively heavy missiles

would tend to hit the ground sooner than calculated on the basis of this equation,

with a consequent reduction in the calculated maximum missile speed.

In spite of the many uncertainties involved, the writers believe that the assumptions

used to estimate the speeds of Table 8 are sufficiently conservative for purposes of

nuclear power plant design. It is the writers' judgement that, although higher values of

tornado-borne missile speeds are conceivable, their probabilities of occurrence, for any

given tornado strike, are low.
9. REFERENCES

1. Paddleford, D.F., Characteristics of Tornado Generated Missiles . Report WCAP - 7897,

Westinghouse Electric Corp. Pittsburgh, Pennsy Ivania , April, 1969.

2. Lee, A.J.H., Design Parameters for Tornado Generated Missiles , Topical Report

GAI-TR-102, Gilbert Assoc., Inc., Reading, Pennsylvania, Jan., 1975.

3. The Generation of Missiles by Tornadoes , TVA-TR74-1, Tennessee Valley Authority,

Nov., 1974.

4. lotti, R.C., Velocities of Tornado-Generated Missiles , ETR-1003, Ebasco Services Inc.,

New York, N.Y., Feb., 1975.

5. Beeth, D.R., and Hobbs, S.H. Jr., Analysis of Tornado Generated Missiles , B&R-OOl,

Brown & Root, Inc., Houston, Texas, May 1975.

6. Meyers, B.L., and Morrow, W.M. , Tornado Missile Risk Model , BC-TOP-10, Bechtel Power

Corporation, San Francisco, Calif., June 1975.

7. Battacharya, A.K., Boritz, R.C., Niyogi, P.K. , Characteristics of Tornado Generated

Missile UEC-TR-002-0, United Engineers & Constructors, Inc., Philadelphia, Oct., 1975.

8. Fung, Y.C., An Introduction to the Theory of Aeroelasticlty . Dover Publications, Inc.,

1969.

9. Scanlan, R.H., "An Examination of Aerodynamic Response Theories and Model Testing

Relative to Suspension Bridges," Proceedings , Third International Conference on Wind

Effects on Buildings and Structures, Tokyo, 1971.

10. Eagleman, J.R., Muirhead, V.U., Williams, N., Thunderstorms, Tornadoes and Building

Damage , Lexington Books, Lexington, Mass., 1975.

11. Markee, E.H., Beckerley, J.G., Sanders, K.E., Technical Basis for Interim Regional

Tornado Criteria , Wash-1300 (UC-11) , U.S. Atomic Energy Commission, Office of

Regulation, May, 1974.

12. Bates, F.C., and Swanson, A.E., "Tornado Considerations for Nuclear Power Plants,"

Transactions , American Nuclear Society, Vol. 10, pp. 712-713, Nov., 1967.

13. Hoecker, W.H., "Wind Speed and Air Flow in the Dallas Tornado of April 2, 1975,"

Monthly Weather Review , Vol. 88, No. 5, 1960.

14. Wortman, A., "Aerodynamics of Randomly Tumbling Bodies," Journal of Spacecraft and

Rockets, AIAA, Feb., 1969, p. 205-207.

15. Hansche, G.E., and Rinehart, J.S., "Air Drag on Cubes At Mach Numbers 0.5 to 3.5,"

Journal of the Aeornautical Sciences , Feb., 1952, pp. 83-84.

16. Hoerner, S.F., Fluid-Dynamic Drag , Published by the Author, 1958.

17. National Design Specification for Stress-Grade Lumber and Its Fastenings , National

Forest Products Association, Washington, D.C., 1973.

18. Garson, R.C., Catalan, J.M. , and Cornell, C.A., "Tornado Design Winds Based on Risk,"

Journal of the Structural Division , ASCE, Vol. 101 No. ST9 , Proc. Paper 11559, September,

1975, pp. 1883-1897.

19. McDonald, J.R., Mehta, K.C. , Minor, J.E., "Tornado-Resistant Design of Nuclear PowerPlant Structures," Nuclear Safety . Vol. 15, No. 4, July-August 1974.

USCOMM-NBS-OC 20
APPENDIX A - EQUATIONS OF MOTION

Al.l Absolute and Translating Frames of Reference

Consider the absolute frame of reference Oj^ xyz (Fig. Al.l) and a frame 0^ x'y'z

such that 0^2 is parallel to Oj^z. It is assumed that the frame O2 x'y'z translates with

respect to 0^^ xyz with a constant velocity, the components of which (in the Oj^ xyz frame)

are (v„ , , 0) . The angle between 0-x' and O.x being denoted by 6 , Tx Tv 2 1 c

""tx

®c - ,2^2 ,1/2 (Al.l)

(^x ^ ^y>

sin 0 Ty ,2.2 .1/2 (A1.2)

A1.2 Vectors of Position

Using the notations of Fig. Al.l, the vectors of position of the particle P in the

absolute and in the translating frame of reference may be written as follows:

Absolute frame (with origin 0^^)

R=xT+yT + zk = r cos 0 T + r sin 0 j + z k (A1.3)

where T, J, k are unit vectors along the axes O^x, O^^y, O^^z respectively.

Translating frame (with origin O2)

R' = x' i' + y' J' + z k - r' cos 0' i' + r' sin 0' J' + z k (A1.4)

where 1?, j', k are unit vectors along the axes O2X' , 02y', 02Z» respectively

A1.3 Transformations of Unit Vectors

The unit vectors r, 0, k of the revolving frame of reference (see Fig. Al.l) may

21
DIRECTION OF

TRANSLATION

Figure Al Notations

22
be written in terms of the unit vectors of the translating frame 02X'y'z and the angle

between the lines O^P and O^x", where O^x" is parallel to O2X' , as follows:

r = cos e' i' + sin e' j'

The

e = -sin 6' i' + cos e' j' (A1.5)

k = k

imit vectors i' , j', k, of the translating frame 0^ x'y'z may be written in

terms of the unit vectors of the absolute frame of reference and of the angle 6^ as

follows:

i = cos e i + sin 6 j

c c*^

j' - -sin e i + cos e j (A1.6)

c c

A1.4 Expression of Wind Velocity in an Absolute Frame of Reference

Let the vortex wind velocity with respect to the translating frame of reference be

denoted v^, and let its components along the vectors r, 9 and k be denoted by v^^. v^g

and v^j^, respectively, i.e..

V " V r + V „ 9 + v , k (A1.7a)

(0 ur u)6 (i)k

With respect to the absolute frame of reference, v^ may be written as v-vl + vj+vk (A1.7b) u ux coy u)Z

The components v , v and v are obtained by substituting Eqs. A1.5 and A1.6 into ux uy (DZ Eq. A1.7a, i.e., in matrix form.

23
ux

0) z

cos e - sin e 0

c c

sin e cos e 0

c c

cos e' -sin e' 0

lin e' COS e' 0

V

V

0)6 (A1.8)

The total wind velocity consists of the sum of the vortek wind velocity and the

translating velocity of the vortex, i.e.,

V i + v J+v, k wx wy wk (A1.9)

where

V V + v_

wx ojx Tx

V "V + v_

wy uy Ty

(Al.lO)

V = V

WZ U)Z

and V , V , v are given by Eqs. A1.8. In Eqs. Al.lO and A1.8, the quantities

v_ , v_ , V . V V , and 6 are specified. The quantity 9

' is a function of time and ix iy lor 0)0 a)K c is obtained from the relations

cos 0 = —

sin e' = ^

r' (Al.ll)

, , ,2 ^ ,2.1/2

y

r ' « (x' + y' )

24
in which x' and y' are determined as explained in the following.

Let the initial conditions of the problem be

t = initial time

o

(x , y , z ) = coordinates of particle at time t in the absolute frame

o o o , o

(v . , v„ ) = velocity components of particle at time t in the

^.PXO' Pyo' PZO J r r q absolute frame

(x02q» y^2o* ~ P°^^^^°° (oJ^^Sin of the translating frame) at time

t , in the absolute frame,

o

At time t, the position vector of the origin O2 is ?

,

= [xO^^ + (t - t^)] i + [y02^ + (t -t^) j]

BO that for any time t >_ t^ we have

(A1.12)

R' = R - RO, (A1.13)

where R=xi+yJ + zk, i.e..

^R'

=R'

xO_ + v„ (t - t ) 2o , Tx p

yO„ '20 + v_. (t - t ) Ty o (Al.lA)

Since

Xr. i + Yr. j + Zr. k = x' i' + y' j' + z' k (A1.15)

it follows, using the inverse of the transformation A1.6,

L z' J L 0

cos 6 sin 6 0

c c

-sin e cos e 0

c c

0

^R-

«- ^R' 25

(A1.16)
where x^^,, y^,, Zj^i, are given by Eq. Al.14. The quantities x', y', z', in Eq. Al.ll, and

thus the quantity 6* in Eqa Al.lO, A1.8 are expressed in terms of the coordinates of point

f with respect to the absolute frame, and of the quantities xO^^,

y02o* ^xx* ^Ty* ^o

^'

The problem of expressing the components In the absolute frame of the wind velocity at point

P (x, y, z) in terms of the vortex wind velocity components v^^, v^^, v^j^, of the translation

velocity components v^^, v^^, of the initial conditions and of the coordinates x, y, z of

the point P Is thus solved.

A1.5 Equations of Motion

The equations of motion nay be trriccen as

1/2 P V!v^Jv^j-gk (A1.17)

where m • mass of particle, p air density, C^^ " drag coefficient, A > area of the particle,

• • • Vj^gj^ - (v^^ - x) 1 + (v - y) T •• <v^^ - z) k, and g - acceleration of gravity.

APPENDIX B - ANALYTIC SOLUTION TO THE EQUATIONS OF MOTION FOR A UNIFORM WIND FIELD.

In the case of a uniform wind field an analytic solution of the equations of motion

of a particle may be obtained as shown herein. This solution was used to test the computer

program, in which the wind field subroutine was suitably modified. The following assumptions

were used

1) The initial velocity of the particle Is zero

2) The notion occurs In the x - z plane only

3) The wind velocity vector Is at all points parallel to the horizontal axis 0^ and

has the constant magnitude v .

26
The equation of motion in the horizontal direction is

where

.2 , „ dx , dx^ 2 . / . o T \ —1 = " ^^w - (^2.1)

dt

^ = I

CjjA, or

f '^(f) = /• a dt + Cj^ ' (A2.2)

With the change of variables u = - v^, du = d Eq A22 becomes

J

^ = a t + (A2.3)

- = a t + (A2.4)

dt

"

Integrating Eq. A2.5, there follows

X = V t - / + (A2.6) w y at + 2

With the change of variables a t + = u, a dt = du, dt = Eq. A2.6 becomes

x = vt--/— + (A2.7) w a /

- u 2

X = V t - - In (at + C.) + C„ (A2.8) w a 1 2

The constants of integration are determined as follows

At t = o , X = X and 4^ = o , i . e .

,

o dt

27
- - - In C- + Co a 1 2 (from Eq. A2.8) (A2.9)

1 ^w- c: (from Eq. A2.5) (A2.10)

Thus

- 7" (A2.11)

V

C- - X In V

2 o a w

(A2.12)

and

x"x + vt ln(avt+l) o w a w

(A2.X3)

28
APPENDIX C

DOCUMENTATION,

AND

SAMPLE INPUT AND OUTPUT

OF COMPUTER PROGRAM

29
TnHNArO** IMM 1 ) .*«A |N«CX ( 1 )

1 C

2 c NATIONAL BUREAU OF STANOAKDS

3 c APPLIFO MATHF.MATICS DIVISION

4 c

5 c TOWWDl

6 c

7 c A FCRTHAN APPLICATIONS PROGRAM TO STUOV THF MUTfGN OF AN OBJFCT

B c UNOCP THE INFLOFNCr OF A TOPNADO W I NO FIFLO,

q c

1 0 c MAWTIN COROES

1

c

1 2 c APRIL 197b

I 3 c

1 4

1 5 c 16 c PU«POSF.

1 f c

I a c THIS FCRTPAN PROGRAM INTFGRATFS IN T I MF THF FOLLOWING EQUATIONS OF

1 Q c MCTICN FOR A RIGID f^OOy ACTED ON RY A DRAG FORCE IN A 20 c GRAVITATIONAL FIFLC*

2 1 c 22 c 0**2(PX» / 01**? = ALPHA * VRX

23 c 24 c 0**2(py) / DT**2 = ALPHA * VRY

25 c • 26 c. 0**2(PZ» / OT*«2 = ALPHA * VRZ - G

27 c 28 c ANO

29 c 30 c Alpha = cd • a * rho * vr / 2 • 31 c. 32 c 33 c 34 c 0**2(X) / 0T»*2 IS THF SECOND DERIVATIVE OP X WITH RESPECT

35 c TO TIME.

36 c 37 c PX ARE THE X. Yt 2 COORDINATES OF THE

38 c PV PARTICLE AS A FUNCTION OF T 1 MF IN THE

39 c P2 ABSOLUTE FRAME,

40 c

4 1 c VRX ARE THE X. Y, Z CUMFCNtNTS OF THE RELATIVE

42 c VRY VELOCITY OF THF WIND WITH RESPECT TO A 43 c VRZ STATIONARY PARTICLE IN THF ABSOLUTE FRAME.

44 c 45 c G IS THE MAGNITUDE OK GRAVITY.

46 c

4"' c CO IS THE DRAG COEFFICIENT.

4a c

4 9 c A IS THE AREA ASSOCIATED *ITH THE BODY.

60 c 51 c RHO IS THE DENSITY OF AIR.

62 c 53 c VR IS SORT (VRX ** 2 VRY » 2 VRZ ** 2).

54 c 55 c THIS SYSTEM CF THREE. SECOND ORDER EQUATIONS IS CONVERTED TO A 56 c SYSTEM OF SIX. FIRST ORDER EQUATIONS BY A STANDARD TECHNIQUE.

5-» c THE rOUfVALENT FIRST ORDER SYSTEM IS INTEGRATED RY THE ODC

30
58 C SOLVP«. . . 5S c 60 c THE COMPONPNTS OF THE PARTICLE VELOCITY AND THE WIND VELnCITY APE

6 1 c *>ITH RESPECT TO AN ABSOLUTE FRAME, ThF WIND VELOCITY IN THE

e2 c ABSOLUTE FRAME IS THE SUM OF THE WIND VELOCITY FRQM A STATIONARY

6 3 c TORNADO VORTEX AND THE TRANSLATION VELOCITY OF THE TORNAOC VGfiTFX.

64 c 65 c INITIAL CONDITIONS,

66 c , 67 c AT TIME = TO THE X, Y, Z COORDINATES AND VELOCITY COMPONENTS

6H c OF THE PARTICLE ARE SPECIFIED, IN ADOITICN, THE X, Y 69 c COORDINATES OF THE ORIGIN OF TmE TRANSLATING FRAME WHICH THE

70 c TORNADO IS STATIONARY IN ARE SPECIFIED,

71 c 72 c CONDITIONS INDEPENDENT OF TIME,

77 c

74 c THE X, Y VELOCITY COMPONENTS OF THE TRANSLATING FRAME ARE

75 c CONSTANT.

76 c 77 c FOR FURTHER DETAILS CONSULT REFERENCE 2),

78 c 79 c APPLICABILITY ANC RFSTr ICT ICNS . 80 c

81 c THIS PROGRAM IS INTENDED FOR WORK THAT REQUIRES MODERATE ACCURACY

P2 c AND MODERATE TIME PERIODS OF INTEGRATION,

83 c 8A c THE CURRENT VERSION PRODUCES PLOTS OF AT MOST 101 DATA POINTS. THE

85 c DATA IS FROM THE TABULAR RESULTS GENERATED AT THE FIRST 10 1 PRINT

86 c STEPS. TO PREVENT A TRUNCATED PLOT FROM BEING GENERATED RE SURE

37 c THAT TIMEIT AND FXTMIT SATISFY T IME IT ,LT , 100 FXTMIT, HLPE

88 c TIMEIT IS THE TIME INTERVAL OF INTEGRATION AND FXTMIT IS THE TIME

89 c INTERVAL BETWEEN SUCCESSIVE PRINT STEPS.

90 c

91 c PROGRAM STRUCTURE.

92 c 93 c SUBPROGRAM DIRECTORY.

94 c 95 c COMMENT ADDITIONAL SUBPROGRAMS OTHER THAN FORTRAN INSTRINSIC

96 c FUNCTIONS AND FORTRAN BASIC EXTERNAL FUNCTIONS

97 c NECESSARY FOR THE EXECUTION CF THIS MAIN PROGRAM ARE

98 c LISTED BELOW IN ALPHABETICAL ORDER. EACH IS

99 c ACCOMPANIED BY A SHORT FUNCTIONAL DESCRIPTION.

100 c

101 c OFUN THIS SUBROUTINE COMPUTES THE RIGHT HAND SIDE OF THE

102 c FIRST ORDER CDE SYSTEM. DY IS THE LOCAL NAME OF OFUN

103 c IN VOAOAM.

1 04 c 105 c DRAG (USER SUPPLIED.) THIS SUBROUTINE COMPUTES THE DRAG

106 c COEFFICIENT.

107 c 108 c INPUT THIS SUBROUTINE READS IN OR CONTROLS THF READING IN OF

109 c ALL RELEVANT DATA AND PARAMETERS EXCEPT THE PARAMETERS

110 c REQUIRED BY THE ODE SOLVER AND WHICH AFFECT OUTPUT,

111 c 112 c OUTPUT THIS SUBROUTINE READS IN PARAMETERS THAT CONTROL WHICH

113 c PLOTS ARE TO BE PRODUCED AND SUPERVISES THE PRODUCTION

1 14 c AF ALL OUTPUT,

115 c

31
I 16 C

I I c

1 1 e c

I 19 c 120 c 12 1 c 122 c 123 c 124 c 125 c 126 c 127 c 12« c 129 c

1 30 c

1 3 1 c

1 32 c 133 c 134 c 135 c

1 36 c

1 37 c

1 3fl c

1 39 c 140 c

1 4 1 c 142 c 143 c

14 4 c 145 c 146 c 147 c

148 c 149 c

1 50 c

151 c 152 c 153 c 154 c 155 c 156 c 157 c 15a c 159 c 160 c 161 c 162 c 163 c 164 c 165 c 166 c 167 c 168 c 169 c 170 c 171 c

1 72 c

17 3 c

PLOT THlf^ SUHROUTINE PRODUCES A (JNt PAGE PRINTP.P PLOT.

TCnWOF (USER SUPPLIED.! THIS SUBHOUTINF COMPUTES THE PAOIAL.

ANGULAR. AND Z COMPONrNTS DF THE *IND AT THE PAWT ICLF

AS MEASURED IN THE TRANSLATING FRAME.

THIGFS THIS SLDMUUTINF COMPUTES THE COSINE AND SINE OF THE

BASE ANGLE OF A RIGHT TWIANGIE ftlTH BASE AND VERTICAL

SIDE GIVEN.

VCADAM THIS SUHHOUT INE IS T HF ODF SOLVtR. EACH CALL DCES ONE

INTEGRATION STEP.

EXeCLTION TREE.

COMMENT THE EXECUTION TRFF IS A STRUCTURE THAT OFSCRIRES THE

SUBPROGRAM INTERACTION DURING EXECUTION. THE TREE IS

COMPOSED OF A NUMBER OF LEVELS. EACH LEVEL IS CCMPOSED

OF ONE OR MOPE BL'JCKS. A BLOCK IS COMPOSED OF A CONTIGUOUS SET OF TREE ELEMENTS. FACH TRFF ELEMENT

HAS THE FORM

NUMHIINAMF. KUMS2

)

WHERE

NUMB I IS THE NUMBER OF THE ELEMENT IN THE

CURRENT LEVEL.

NAME IS THE NAME OF ThF SUBPROGRAM ASSOCIATED

WITH THAT ELEMENT

,

NUMB2 IS THE NUMBER OF THE FIRST ELEMENT OF

THE BLOCK AT THE NEXT GREATER LFVEL WHICH

CONTAINS ALL SU^P'^OGPAMS CALLED DV

SUBPROGRAM NAME. IF NUMH2 IS ZERO THFN

SUBPROGRAM NAME CALLS NO SUBPROGRAMS.

LEVEL 0

KMAIN • I)

LEVFL 1

ic INPUT • n

2(VOADAM, 4)

3 (OUTPUT. 5)

LEVEL 2 KTORWDF, 0»

2 (DRAG . 0)

3(TRIGFS. 0)

LEVEL 3 U TORWDF . 0) 2 ( OR A G . 0 ) 3(TRIGFS, 0)

4(0FUN .

5( TOR WDF , 6(CRAG . 7 { TRI GFS,

8(PL0T ,

1 )

0)

0)

0 » 0 > PROGRAM I/O.

I NPUT.

ROUT INE.

MA IN INPUT

LOGICAL UN IT (S ) .

5

5

EXECUTION TREE ELEMENT

LFVEL 0, ELFMLNT 1

LE VEL 1 « ELEMENT I

32
174 C

l-'S C OUTPUT 5 LFVFL 1. ELEMENT 3

1 76 C

17-r c TOR*DF 5 LEVLL 2, ELEMENT I 178 c

17<5 c DRAG 5 LEVEL 2, ELEMENT 2

leo c

1 ei c OUTPUT,

182 c 183 c ROUTINE. LOGICAL UNIT(S), EXECUTION TREE ELEMENT.

164 c 185 c HA IN 6 LEVEL 0, ELEMENT 1

1 86 c 187 c OUTPUT 6 LE VEL I , E LE ME NT 3 lea c 189 c TCBWDF 6 LEVEL 2. ELEMENT 5

190 c

1<31 c DRAG 6 LEVEL 2. ELEMENT 6

192 c 193 c PLOT 6 LEVFL 2. ELEMENT 8

194 c

1 95 c PROGRAM USAGE (INPUT).

196 c 197 c DATA GROUPINGS.

198 c 199 c GROUP 1

.

200 c

20 1 c SUBGROUP 1.1. TORNADO WIND FIELD PARAMETER CARD( S)

.

202 c 203 c CARD. VARIABLE LIST. F ORMAT . 204 c 205 c SEE SUBROUTINE TORWDF FCR ThE EXACT SET OF PARAMETERS

206 c TO READ IN AND THEIR FORMAT.

207 c 208 c SUBGROUP 1.2. DRAG COEFFICIENT PARAMETER CARD(S).

209 c 210 c SEE SUBROUTINE DRAG FOR THE EXACT SET OF PARAMETERS TO

211 c RE AC IK AND The IP FORMAT.

212 c 213 c GROUP 2.

2 14 c 215 c SUBGROUP 2.1. PARTICLE PARAMETER CARD.

216 c 217 c CARD. VARIABLE LIST. FORM AT

.

216 c

2 19 c 1 AREA. MASS 2C 12 .0

220 c 221 c VARIABLE DEFINITION TAHLF (GROUP 2).

222 c 223 c AREA ARE THE AREA. MASS UF THE PARTICLE.

224 c MASS

225 c 226 c GROUP 3.

227 c 228 c SUBGROUP 3.1. INITIAL CONDITION CARDS.

229 c 230 c CARD. VARIABLE LIST. FORMAT

.

231 c

33
23? C I XPO, YPO , ZPO, VXPO« VYPO, VZPO hF\?,0

233 C 234 C 2 XOTFt YOfF , VXTF, VYTF, TO 5F12.0

?3S C

23ft C SU8GH0UP 3.?. FINAL CONDITION CARD.

2 3T C 23R C 3 TIMFIT E12.0

23q c 240 C SUBGROUP 3,1. OOE SULVFP PARAMETER CAPO.

241 C ' : . 242 C . 4 HI. FXTMIT, EPSI 3ei2.0

243 C

244 C SUBGROUP 3.4. PLOT AND VALIDATION PrtAMETTP CARO.

245 C 246 C .5 WTPT2Y, WTPTYX, WTPT7X, WTPTXT. 712

J47 C WTPTSX. WTPTHT. WTVALO

248 C 249 C VARIABLE DEFTMTICN TABLE (GROUP 3).

250 C

251 C . , XPO ARE T»-E INITIAL X. Y, Z CC.OROINATES HE THE

252 C YPO PARTICLE.

253 C ZPO

254 C

255 C VXPO APE THE INITIAL X» Y, Z VELOCITY COMPONENTS OF

256 C VYPO THE PARTICLE.

257 C VZPO

258 C

259 C XOTF ARE THE INITIAL X, Y COORDINATES OF THE ORIGIN

260 C YOTF OF THE TRANSLATING FRAME *HICH THE TORNADO IS

261 C STATICNARY IN.

26? C

263 C VXTF ARE THE CONSTANT X. V VELOCITY COMPONENTS OF THF

264 C VYTF TRANSLATING FRAME.

26 5 C

266 C . TO IS THE INITIAL TIME.

26-^ C

268 C TIMEIT IS THE INTERVAL OF INTEGRATION.

269 C

270 C HI IS THF INITIAL TIME STEP, A GOOD VALUE TO USE

271 C IS I .OF-4

272 C

273 C FXTMIT CONSTRAINS THE ODE SOLVER TO PRODUCE RESULTS FQi^

274 C PRINTING AT EQUALLY SPACED TIME INTERVALS OF

275 C THIS SIZE.

276 C

277 C EPSI IS THE LOCAL ERROR TOLERANCE USFO BY THE ODE

278 C SOLVER. A GOOD VALUE TO USE IS l.OE-4.

279 C

280 C THE NEXT 6 VARIABLES ARE FLAGS FOR PRODUCING PLOTS. IF 28 1 C A FLAG IS SET TO 1 THE CORRESPONDING PLOT IS PRODUCED.

282 C OTHERWISE. THE PLOT IS NOT PRODUCED.

283 C

284 C VKTPTZV IS THE FLAG FOR A PLOT CF 2 VERSES V.

285 C 286 C VkTPTYX IS THE FLAG FOR A PLOT OF Y VERSES X.

287 C

288 C WTPTZX IS THE FLAG FOR A PLOT OF Z VERSES X. 289 C

34
29 0

2Q1

29 2 293

29 4 295

2Se

297

298

299

300

30 1 202

303

304

3 05

2oe

30-^ 308

309

31 0 31 I 3 12

313

314

315

316

317

318

319

320

321

322

323

324

325

226

327

328

229

330

231

332

3? 3

334

335

236

337

338

339

34.0 341

342

34 3

344

245

346

34 7

Cc

c

cc

c

c

cc

c

c.c

c

cc

c

c

c

cc

cc

cc

c

cc

c

c

c

cc

cc

c

cc

c

c

c

cccc

c

cc

c

cc

cc

cc

cc

cc

WTPTXT IS THE FLAG FOR A PLOT OF X Vfc'RSFS TIME.

WTPTSX IS THE FLAG FDR A PLOT QF SPEED VERSES X.

(KTPTHT IS THE FLAG FOR A FLCT OF HCRIZONTAL SPFED

VFRSFS TIME.

WTVALD IS A FLAG WHICH IF SF T TO 1 CAUSES VALIDATION

INFORMATION TO BE PRINTED IN ADDITION TQ THE

LSUAL OUTPUT AT EACH PRINT STEP. OTHERWISE.

NO EXTRA OUTPUT IS GENERATED.

DECK STRUCTURE.

COMME NT

INDEX •

1

2

3

4

WHAT FOLLOWS FACH INDEX NUMBER BELOW MUST START A NEW

CARO.

CARDS

.

GROUP 1. GRCUP 2.

GROUP 3.

SENTINEL.

STL OOP (FIRST USE).

FORMAT.

SEE A30VE.

SEE ABOVE.

SEF ABOVE.

12

STLOGP IS AN INTEGER VARIABLE SET TO A SENTINFL VALUE. IF STLOOP IS 1 THEN THE

CARDS THAT FOLLOW ARE OBTAINED BY

RFCURSIVFLY STARTING AT INDEX 3.

OTHERWISE, THE NEXT SFNTINEL CARD IS

READ.

SENT INEL • STLCOP (SFCONC USE).

12

STLOOP IS AN INTEGER VARIABLE SF T TO A SENTINEL VALUE. IF STLOOP IS 1 THEN THE

CARDS THAT FOLLOU ARE OBTAINED BY

RECURSIVELY STARTING AT INDEX 2.

OTHERWISE, THE NEXT SENTINEL CARD IS READ.

SENTINEL.

STLCOP (THI RD USE)

.

12

STLOOP IS AN INTEGER VARIABLE SET TO A SENTINFL VALUE. IF STLOOP IS 1 THEN THE

CARDS THAT FOLLOW ARE OBTAINED BY

RFCUSRIVELY STARTING AT INDEX 1«

OTHERWISE, THE RUN IS COMPLETED.

EXAMPLE.

35
34 « C 349 C GROUP I CARO( S)

.

350 C GROUP 2 CAPO,

351 c GROUP 3 CARDS.

352 c 1 353 c GROUP J CARDS.

354 c 0

355 c 1 356 c GROUP 2 CARD.

ss-' c GROUP 3 CARDS.

358 c > 0

359 c 0

360 c 1 36 1 c GROUP 1 CARD! S)

.

36 2 c GROUP 2 CARD.

363 c GROUP 3 CARDS.

364 c • 36 5 c • 366 c • 36"' c 0

368 c 0

369 c 0

370 c 371 c STRUCTURF OF USER SUPPLIED SUBPROGRAMS.

272 c 37 3 c THE DEFINITION OF THE CALLING PAHAMETFWS USFO IN USER SUPPLIED

374 c SUBRCUTINES TOHV»CF AND DRAG CAN BE PHTAINEO FROM THE CURRENTLY

375 c SUPPLIED VERSIONS OF THESE ROUTINES.

376 c 377

378 c 379 c SUBROUTINE T ORV* OF ( RPT F , COSPTF, SINPTF, ZPTFt VRWTFt VAVnTF,

380 c

• VZWTF « WH I CH6

)

38 1 c 382 c DECLARA TI CNS.

383 c 384 c GO TO (100 . 500. 1000). VKHICHG

385 c 386 c too SECTION FOR HEADING IN PARAMETERS TO BE USF.D IN THIS

387 c SUBROUTI NE.

3P8 c 389 c KFTURN ' 290 c

39 1 c 500 SECTION FOR COMPUTING THE VELOCITY COMPONENTS OF THE

392 c TORNADO WIND FIELD.

393 c 394 c RETURN

395 c 396 c 1000 SECTION FOR PRINTING ANY RELEVANT PARAMETERS USED IN THF

397 c CCMPUT AT ION.

39 8 c 39 9 c RETURN

400 c END

401 c 402

402 c 404 c SUBROUTINE ORAG{PARMTSt DRAGCF , wHICHGI

405 c

36
406 C DECLARAT ICNS

.

407 C

408 c GU TO (100, 500, 1000), WHICHG

409 c 410 c 100 SECTICN f^CP HEADING IN PARAMFTEHS TO BE USED IN THIS

41 1 c SUtJRCUTI NE.

412 c 413 c RETURN

414 c 415 c 500 SECTION roR COMPUTING THE DRAG COEFFICIENT.

416 c 417 c RETURN

418 c

41<9 c 1000 SECTICN FOR PRINTING ANY RELEVANT PARAMETERS USED IN THE

420 c COMPUTATI ON.

421 c 422 c RETURN

421 c END

424 c 425

426 c 427 c PRCGRAf USAGE (OUTPUT).

42« c

42C} c LAYCUT OF OUTPUT,

4 30 c 431 c THE PROGRAM OUTPUT IS BROKEN INTO 4 SECTIONS.

432 c 433 c SECTICN 1. PROBLEM DESCRIPTION,

434 c 435 c ThE FCLLOWING DESCRIPTIVE INFORMATION IS PRINTED.

43e c 437 c WIND VELOCITY PARAMETERS.

43e c 43q c ALL THE PARAMETERS WHICH ARE INPUTEO FOR COMPUTED THE

440 c TORNADO WIND FIELD ARE PRINTED. THE NUMBER, NAMES, AND

441 c MEANING OF THE PARAMETERS ARE DETERMINED BY THE USFR.

442 c 443 c DRAG COEFFICIENT PARAMETERS.

444 c 445 c ALL THE PARAMETERS WHICH ARE INPUTED FOR COMPUTING THF

446 c DRAG COEFFICIENT ARE PRINTED, THE NUMBFR, NAMES, AND

447 c MEANING OF T(-E PARAMETERS ARE DETERMINED BY THE USER.

448 c 44q c PARTICLE PARAMETERS.

450 c 451 c SELf-F XPLANATORY . FROM INPUT.

452 c 453 c INITIAL CONDITIONS (TORNADO WIND FIELD).

454 c 455 c SELF-EXPLANATORY. FROM INPUT.

45 6 c 457 c INITIAL CONDITIONS (PARTICLE).

45a c

45<; c SELF-EXPLANATORY. FROM INPUT.

460 c 461 c SECTION 2. TABULAR RESULTS.

46? c 46 3 c FIRST. THE INITIAL TIME AND THE TIME INTERVAL FOR OUTPUT ARE

37
4^ A Q PRINThO. NFXT, 13 COLUMNS OF OUTPUT AHF GFNErtATtO. EACH L I NF

465 c CORRESPONDS TO A SINGLE PPINT STEP. THF MEANING OF EACH

t_ c c COLUMN IS AS FCLLOWS.

46 7 46 8 c N S TP IS THE INTEGRATION STEP NUMBER REACHED AT TIME

4 ^ S T . 4 7 c

4 71 T IS THE SIMULATED TIME AT WHICH OUTPUT IS

4 72 c GENERA TED

4 7 3 4 74 " XP ARE THE X, Y, Z CCCRDlNATFS OF THE PARTICAL IN

4 75 YP THE ABSOLUTE FRAME AT TIME T.

4 7 6 ZP

4 7 7 478 c R ( X Y ) IS SQRT(XP ** 2 YP ** 2).

4 79

4R0 c VXP ARE THE X. Y. Z CCI^PQNENTS OF THE PARTICLE

48 I c V YP VELOCITY IN THE ARSOLUTE FRAME AT TIME T,

4 B2 c V ZP

4 P ? 4B ^ HSP EEO IS SOHlT(VXP * ? VYP ** 2)

4 3 5 c

4 R6 SPEED IS SqRT(VXP **?* VYP * 2 + V7P ** 2)

4 8 7 4 R8 c H W S P E F D IS THE HORIZONTAL SPFFD OF THE TORNADO WIND AT

4r)9 c THE PARTICLE IN THF ABSOLUTE FRAME.

490 c 49 1 c RTF<XY

)

IS THF HORIZONTAL DISTANCE OF THE PARTICLE FROM

492 c THE ORIGIN OF THE TRANSLATING FRAME.

49 3 c 494 c IF WTVALO = 1 THEN ADDITIONAL OUTPUT IS GENERATED AT EACH

495 c PRINT STEP . SEE THE VALIDATICN SECTION FOR THE MEANING OF

496 THIS ADDITIONAL OUTPUT.

497 c 49 S c SECTION 3. PROBLEM TERMINATION.

499 c 500 c FIRST, THE REASON FOR TERMINATION IS PRINTED. IT CAN BE FOR

50 1 Q ONE OF THREE REASONS.

E 02 Q

£ 03 Q 1 ) THE FINAL TIME HAS DFFK REACHED.

50 4 Q

505 Q 2 ) THE PARTICLE HIT THE GRCUND,

506 c 50 7 c 3) THE ODE SOLVER FAILED PPEMATURFLV,

5 0 fi c 5 0 9 NEXT, RESULTS RELEVANT TO THE *HCLF RUN ARE PRINTED. EACH IS 510 c CURRENTLY TAKEN TO BE THE MAX IMUM IN ABSOLUTE VALUE OVER

511 c VALUES GENERATED AT THE PRINT STEPS. THEY HAVE THE FOLLOWING

512 MFANI NG.

513

514 c MAXVXP ARE THE MAXIMUM X, Y, 7 COMPONENTS IN ABSOLUTE

515 c MAXVYP VALUE OF THE PARTICLE VELOCITY IN THE ABSOLUTE

516 MAXVZP FRAME . 5 17

518 c MA XMVP IS THE MAXIMUM SPEED OF THE PARTICLE IN THF

51 9 c ABSOLUTE FRAME.

520 c

52 1 c SFCTIGN 4. PLOTS.

38

J
!

i

f- = 0 T c /FRfl DR MPRF PI D T AHt- PRnDlirFP f 1 NF PFR PARF« T HP HRDlNATt

524 AND AdSCISSA LAHELS CAN gF FCUND CENTFPED BFrLOW THE GRAPH.

525 c THE: PLOTTING CHARACTF.R IS THE LETTER X. AS NOTED IN THE

526 SECTION. APPLICABILITY AND RE S Tk I C T 10 N S AT MOST 101 DATA

527 c POINTS ARE PLCTTED.

528 c

c o c f\^ « O U c

7 O 1I f INPUT rJ-FTKINR.

53 3 THE FOLLOWING VARIABLES ARE CHECKED FOt^ VALIDITY IN THE MAIN

534 PROGRAM* IF AT LEAST ONE IS INVALID AN ERROR MESSAGE IS PRINTED

535 AND THFY ARE ALL RE SF T TO DEFAULT VALUES. THE DEFAULT VALUES

536 CAS BF FOUND IN THE SECTiCN. MACHISE/SYS TFM DEPENDENT FEATURES*

£3T c AT THE START OF THE EXECUTABLE C TDE IN THIS MAIN PROGRAN'.

53 8 539 HI IS THE INITIAL STEP. IT MUST BE POSITIVE AND LESS

540 c THAN FXTM I T. 541

542 Q FXTMIT IS THE TIME INTERVAL USFO FOB OUTPUT. IT MUST BE

543 pns IT I VF a £4 4 £45 c PROGRAM DETECTABLE ERRORS*

£46

547 c AFTFR EACH INTEGRATICN STEP THE VARIABLE lER IS CHECKED. IF

54B c ITS VALUE INDICATES THAT THE LAST STEP FAILED THEN INTEGRATION

549 c TERMINATES PREMATURELY* THE REST OF ThF OUTPUT IS GENERATED

b:<% DO nu 55

c WILL REFLECT ONLY RESULTS GENERATED UP TC THE TIME OF THE

5 52 P C ROD . 5 5 3 554 DisrussiuN nF method and ai gorithm.

ec;5 556 c THE PROBI EM Tn HE SnLVFD IS A NUMFPICAL INITIAL VALUE PRTHLEM IN

557 ORDINARY DIFFERFNTlAl EQLjATION"^. SIX. FTR^T CHDFK. ORDINARY

556 <- DIFFFRFmTIAI FOUAT inN^. HF PRF SFN T I Nf; Th f- FOUATfnN^ flF MflTfriNl. ARF

559 c INTEGRATED ft • ^ % 1 >«J r» 1 u_ FROM i SOMF U >^U— Ift NI ^ Ift TI Ift AI^ ^_ T1 1ft MFi_ WITH Vf ft | • t SPFCIFTED j i _ \^ ft i i_ (_/ INITTIAI ft TN ft • ft ft~ 560 Q misjniTIONS TO SnMF LATFR time V^HICH SATISFIES SOMF TFRWINATinN

561 rCNO Va ^ 1 ^ Ift T1 Ift CU N.1 ^ V 562

563 c THE ODE SOLVER* VOADAM* IS BASFD ON THE VARIABLE ORDER* VARIABLE

564 STEP ADAMS fPCF CFSirNFT ANn I MPI EMFNTATFD PY C. W. GFAR IN 565 RFFFRFNCF 1 ) . S I Nf" F THF- tiV'^TFM OF ODFS TP HF «ini VFD I NFN — ^TIFF

566 AI 1 PARAMFTFRS AND r" AI 1 S TO SURRHUTINFS RFOI IRFO FOR c;ni U I ^slr; 567 STIFF SYCTFM^ HAUF RFFN OFl FTFO.

568 /- 569 CN EACH CALL TO VOADAM THF DDF SOI VFR IS ASKED TO INJTFGRATF THF

570 ^YSTFM of onFS nVFR a STFP Of I FNiHTt-i H. THF V AI lIF OF H AWI'iF"^ FROM

571 CNF flF T l«n SOllRrFS.

572

573 Q 1 ) THF VAI liF nF H RFTIIRNFD RV THF PRFv/IHl S C AI 1 OF VOADAM.

574

575 c £? 9) TH1 n F VAw ^ 1w (JE w t. CF^« H'I SPFCIFIFD j~tv»ftFfti_L' Hv'.JT CAIIFR *— ^ 1 t_ Ti NIN TFR I L ACT ^ ^ 1 ^I Ou MIN .• 576

577 c SOURCE 2) IS USED ONLY FOR THF INITIAL STEP AND WHEN THE STEP

578 c IS MODIFIED SC THAT IT FALLS ON A MULTIPLE OF THE FIXED TIME

579 c INTERVAL USED FCR PRINTING. CTHEfiwISE, SOURCE I) IS USED SO AS TO

39
50 0 C ACHIEVE AN FCCNCMICAL I NT E G^^ AT lO N . 56 I 58 ? C

c THE INPUT VALUE OF H IS USED UNLESS THE FQPCR CRITERIA CANNOT RF

5 H 3 c MET. IN THIS CASE THE STEP AND/ CP OfiDEW AWE MDCIFIED TO TRY TO

5 84 c MEET THt ERROR CRITERIA, IF AN ATTEMPT IS MADE TO REDUCE THE STFP

585 c BELOW A CALLER SUPPt. IFO VALUEt HMIN, rnf (JOE SOLVER QUITS AND

5P6 c RETURNS THE APPROPRIATE N0N7ER0 EHKCW CINOITION CODE.

58 7 c 58 8 c ONCE A SUCCESSFUL STEP HAS HEEN TAKEN, VOAOAM ESTIMATES AND

5fly c RETURNS A GCOD VALUE OF h TO BE USED FOR THE NEXT STEP. THIS

590 c EST IMATED STEP CANNOT RE GREATER THAN A CALLER SUPPLIED VAtUF,

591 c HMAX . 59;? c 59 3 c FOR MORE DETAILS UN VOAOAM CONSULT THE MACHINE READABLE

5 94 c OOCUMLNTATI GN AT THE BEGINNING OF THE SUBROUTINE.

595 c

£ 9 6 c VAL lUAT ICN.

59 7 c 59 fi c THE PWOGRAM FRCVIDES THE USER BY WAY OF THE WTVALO INPUT VARIABLE

599 c THE CAPABILITY OF PRINTING IMPORTANT INTERMEDIATE QUANTITIES.

f>0 0 c THESE QUANTITIES ARF PRINTED AS ADDITIONAL OUTPUT AT THE NORMAL

6 01 c PRI NTI NG STEPS. THE AMOUNT OF OUTPUT PER PRINT STEP INCREASES FROM

60 ?. c ONE LINE TO SEVEN LINES. TO INTERPRET THE MEANING OF THE VARIABLES

eo3 c PRINTED CONSULT THE TABLE BELOW ACCOMPANIED BY APPENDIX A OF

604 c REFERENC E 2 > . 6 0S c 606 c R TF IS THE CYLINDRICAL RADIUS OF THE ORIGIN OF THE

607 c TRANSLATING FRAME FROM THE ORIGIN OF THE AHSCLUTE

608 c FRAME

.

609 c 610 c COSTF ARE THE COSINE, SINE OF THE ANGLE THAT THE DIRECTION

6 11 c S INTF CF TRANSLATION MAKES W|TH THE X AXIS OF THE ABSOLUTE

6 12 c FRAME , 613 c

6 14 c PRTF IS THE CYLINDRICAL RADIUS OF THE PARTICLE FROM THF

6 15 c ORIGIN OF THE TRANSLATING FRAME.

6 16 c 617 c FCUSTF ARE THE COSINE. SINE OF THE ANGLE THAT THE CYLINDRICAL

6 18 c PSINTF RADIUS TO THE PARTICLE MAKES WITH THF X AXIS OF THE

6 1 9 c TRANSLATING FRAME.

62 0 c 62 1 c WRTF ARE THE RADIAL, ANGULAR, AND Z COMPONENTS OF THE WIND

622 c WANGTF VELOCITY AT THE PARTICLE USING THF REVOLVING FRAME.

623 c 1*2 TF

6 2 4 c

6 2 5 c taXTF ARE THE X, Y COMPONENTS OF THE HIND VELOCITY AT THE

626 c WYTF PARTICLE USINC THE TRANSLATING FRAME.

627 c 62 8 c WX AF ARE THE X, Y, Z COMPONENTS OF THE WIND VELOCITY AT THE

6 29 c WYAF PARTICLE USING THE ABSOLUTE FRAME.

6 3 0 c WZAF

63 1 c 632 c U VXPAF ARE THE X, Y» Z COMPONENTS OF THE RELATIVE VELOCITY OF

633 c RVYP AF THE PARTICLE WITH RESPECT TO THE WIND USING THE

634 c P VZPAF ABSOLUTE FRAME.

635 c 636 c 637 c PORTABI LI TY.
!! 6je- c

1 c language: . 640 C

€1 C t'FLL VERIFIEH FCRTHAN.

I 642 C

643 C PRECISION,

j 644 C

j e45 C SINGLE.

I 646 C

64 7 C RESTW I CT IONS . 64fl C

i 64g C THIS PkOGRAM #(A S DtSIGNFO TO KUN CURRFCTLY WITH A MINI^'UV CF

i 650 C VGDIFICATIGN ON MACHINES WHICH HAVfl A SINGLE PRECISION

I 651 C FLOATING POINT WORO WITH A MANTISSA IN THE RANGE OF 24 THROUGH

ll 652 C 48 BITS.

653 C

654 C ALL INPLT IS FROM FORTRAN FORMATTED CARD IMAGES AND IS READ

655 C FROM LOGICAL UNIT 5.

656 C

657 C ALL OUTPUT IS FORTRAN FORMAT GfcNFRATEO AND IS WRITTEN TC

658 C LOGICAL UNIT 6. THE INTENChO OFv ICE IS A LINE PRINTER SET TO

659 C AT lF AST A 132 CHARACTERS PER LIKE ANO AT LEAST 60 LINES PER

660 C PAGE.

661 C

662 C FOR FURTHER DETAILS SEE THE SECTION, MACHINE/SYSTEM DEPENDENT

663 C FEATURES. AT THE BEGINNING OF THE EXECUTABLE CODE IN THIS MAIN

664 C PROGRAM AND ALL SUBPROGRAMS LISTFO IN THE SURPROGRAM DIRECTORY,

665 C

I 666 C CCOF RESPCNSI 8IL ITY

.

667 C

668 C MARTIN CORDES

669 C APPLIED MATHEMATICS DIVISION

670 C NATIONAL flUREAU OF STANDARDS

671 C WASHINGTON, O.C. 20234

67 2 C

671 C 1301) 921-2631

674 C

675 C HISTORY.

676 C

677 C ORIGINAL VERSION.

678 C

679 C MAY 1975

680 C

661 C REVISED VERSICN(S).

6fl2 C

683 C AUG 1975

684 C APR 1976

685 C

686 C REFERENCES.

687 C

688 C 11 C. W. GEAR, NUMERICAL INITIAL VALUF PROBLEMS IN ORDINARY

689 C DIFFERENTIAL EQUATIONS, PRENTICE-HALL, 1971, 253P.

690 C

691 C 2) E. SIMIU AND M. COROES. TORNADO - BORNE MISSILE SPEtDS,

692 C NBS INTERAGENCY REPORT

693 C

694 C

695 C

41
TORNAOC*W INC ( 1 ) .TCKWOF $FX ( 0 ) SUBRCU T I NF T C K WOF ( fiP T F , C 03 PT F , S INPTF . ^PTr,V«WTF,VAWTF,VZ*TF.

» WHICHO)

THIS SLBRCUTINE COMPUTES X t-f: TCRNADO V.tNO VtLOCITY COMPONFNTS

DFFIMTICNJ OF PARAMETERS.

RPTF .COSPTF, SI NPTF , ZPTF = RADIAL CCCRDINATB, COSINF AND SINE OF

THE ANGLL , AND Z CCCROINATE OF THE

^ARTICLE WITH RESPECT TO THE CYLINDRICAL

COORDINATE SYSTEM DEFINED AS ThF

J

. TRANSLATING FRAME

VR WTF , VA WTF , VZWTF = RADIAL, ANGULAR, AND Z COMPONENTS OF THE

WIND AT THE PARTICLE AS MEASURED IN THE

TRANSLATING FRAME

WHICHG = 1 - READ IN WIND VFLOCITY PARAMETERS

. , 2 - COMPUTE '*IND VELOCITY COMPONENTS

3 - PRINT WIND VELOCITY PARAMETERS

PARAMETER DECLARATIONS.

REAL RPTF, COSPTF. S INPTF ,ZPTF , V R W TF , V A W TF , VZ Vn TF

INTEGER \»HICHG

CTHER COMMON VARIAGLES.

REAL RMTVZO .MTV.K I ,K?,K 3.K4, K5

COMMON / TWDFDR/RMT VZO .MT V ,K 1 ,K2 , K3 , K4 , K5

LOCAL VARIABLE DECLARATIONS.

REAL RMTVZ ,R33Z ,RAT 10

INTEGER ID.QO

MACHINE/SYSTEM DEPENDENT FEATURES.

DEFINITION OF I/O UNITS USED IN THIS SUBROUTINE.

10 IS THE UNIT USED FOR INPUTING DATA.

CD IS ThE UNIT USED FOR OUTPtJTiNG RESULTS.

DATA ID. OD/5 , 6/

GO TO ( 100,500, 1000> ,«^H1CHG

READ IN WIND VELOCITY PARAMETERS

100 REAC(IC.250) RMTVZO , MTV ,K 1 , K2 ,K3 ,K<» , K5

250 FORMAT( 1 CES. 0)

RETURN

I2

3 C 4 CC

6 C

7 C

8 C

C

1 0 C

1 1 c

1 2 c

1 3 c

1 A c

1 5 c

1 6 c

1 7 c

1 e c

1 c 20 c

2 1 2 2 23 c 24 c 25 c 26

2 7 c 28

2<5 c 30 c

3 1 c 32

34 c 35 c 36 c

3 7 c 38 c

3<; c 40 c

4 1 c 42 c 43 c 44 c 45 c

4 e 47 c 4 8 c 4S c 50 c 51

52 c

5 3 c 54 c 55

56

57

42
56

5Q

60

6 1 f>2 63

64

^ 5 66

67

6°l 69

70

71

72

73

74

75

76

78

79

80

e t 82

B3

84

85

86

87

88

89

90

91

100

1 0 1 102

END PBT

COMPUTE WIND VELOCITY COMPONENTS

500

525

550

575

IF( ZPTF . GE . 60 . 0 ) GO TO 525

RMTVZ=RWTVZO Kl ZPTF

GC TO 550

RMTVZ=RMT VZO+K I 60.0

P33Z= ( WTV/33 .0 ) .625*RMTVZ

IF (RPTF. GE .RMTVZ » GO TO 575

NATI 0=RPTF/RMTVZ

GO TO 6C0

HAT IC = RMTV2/RPT F IF ( RPTF.GE.R33Z ) GO TO 650

600 IF ( ZPTF , GE .60 .0 > GO TC 625

VR WTF=-K5^(R33Z-RPTF )/(HJ3Z- RMTVZ) *RPTF

VAV»TF=R AT IO*MT V V7V»TF=K3+ {R33Z-RPTF)/ ( R3 3Z-PMTVZ ) ZPTF K4/ 3 .0 VAWTF

RETURN

625 IF( ZPTF. GE. 240.0) GO TO 650

VRHiTF=-K5^( R33Z-RPTF ) / (R3 3Z-KMTVZ ) PP TF ( 240. 0-ZPTF) / I 80.

VA*TF=RATI C+WTV

VZVgTF=( l,3 3-ZPTF/180.0)^(K3^(F!J3Z-NPTF)/(H3 3Z-RMTVZ)^60.0

* K4/3 .0 V AWTF ) RETURN

650 VRi«TF=0.0

V AV>TF = RAT lO^MTV

VZ ViiTF = 0. 0 RETURN

PRINT WIND VELOCITY PARAMETERS

1000 VKRI TF ( 00 . 1 1 00 ) WMTVZO ,MTV .Kl .K2,K3.K4,K5

92 1100 FORMAT! 26H0W INO VELUC ITY PARAMF TE 93 * 6X.15H RMTVZO . 1PE12.4/

94 5X.15H f'TV , IPE I 2. 4/

95 5X . 1 5H Kl . IPE 12. 4/

96 * 5X.15H K2 , IPEl 2.4/

97 5X, 1 5H K 3 . IPE 12.4/

98 * 5X . 1 5H K4 , IPEl 2 .4/

99 * £ X , 1 5H K 5 .IPE12.4 ) RETURN

FND

fflPRT ,5 F 1 ,CRA6*EX

43
TOPNAOn* Vk I NU ( 1 ) . OPAG Eh X ( 0 )

1 oUnKUU T I Nr L>RAC>fHAKM lit UN t>v r •MMlCMol

C

3 c

* c

c

c

AiTCC-'^T T Lj 1- /"OAJDllT AT ItfltJ ntT T MP HO A P c t*lrrr It- IrNT

c

I 0

I 1 uiM 1 ri-4 = 1 - RF An T M DP Afl rnf i- FiriKNiT PARA MF TL c ?£ — rnMPiJTF \. X J '1 \j 1 r DRAHr4 rnfFFiriFwT \«'Jl«» IV- - •

I 3 i. "I — PRIMT P'RAT* rnFPFf/'IFMT PA OAMFTPK^

1I A*» f

1 ~ c DADAMFTFP HTPl ADATrrK.-^.

1 A I f> V. 1 f HtAL LJCAlCACJfciTC/l% HAKprlT^ll f

I fi K r AL UK A vA. r

I V INit-tjrHwr'iCrivj

o t £ 1 V- fiTi-iFD ^riMiMnKj WAtJiAm f^q^

C. w DF A 1 r I"^© c

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K. 3 7 c lU lb T Ht. UNIT UStiU rUK INPUTING O A 1 A • 3 e 39 K. L U I 3 1 Ml:. UN IT U oP L' rUK U^^TKU'l f^t> Kr. OUL'

4 C c

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4 ^ ATA lC» OD/^TS* O/^ 4 3 c

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52 2 O CJ p UHMA T I or. 1 ^ • O 1 53

54 c 55 c COMPUTE 0«AG COEFFIC lENT

56 c 57 50 0 DRA GCF-CDRAG

44
5P RFTLRN

c q c

60 c PRINT DPAG COEFFICIFnT PARAMETERS

t I c 6? 1000 «tRITE(OC«l 100 ) CORAG

6 3 1100 FORMA T( 29H0DRAG COEf-FICIENT PARAytTEHS./

64 * 5X,15H CDRAG = ,1PE12.A>

e

= RETURN

66 c 67 END

END PRT

aPPT.S Fl.CATASEX

45
TCRNADQ*teIKO(l) .CA>TA*fcX(l )

1 46. C 130.0 0.0 0.0 1.0 1.0 1.0

2 1 .0

3 1.0 10.0

4 46.0 0.0 40.0 0*0 0.0 0 .0 5 0.0 0.0 35.0 0.0 0.0

6 10.0

7 l.Or-4 l.OE-1 l.OE-4

a 1 1 1 1 1 I 0

s c 10 c 11 0

END FRT

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NBS-n4A (REV. 7-73)

U.S. DEPT. OF COMM.

BIBLIOGRAPHIC DATA

SHEET

1. m HI.K A l lON OK KI I'OR I' NO.

NBSIR 76-1050

2. Cii>v 'l Ac c'C's.s ii) No.

3. Ri i I pu nt ' s Ai L c.''sion No.

4. TITLli AND SUBTITLli

Tornado-Borne Missile Speeds

5. Publication Date April 1976

6. Performing Organization Code

7. AUTHOR(S)

Emil Simiu and Martin Cordes

8. Performing Organ. Report No. WBSIR 76-1050

9. PERFORMING ORGANIZATION NAME AND ADDRESS

NATIONAL BUREAU OF STANDARDS

DEPARTMENT OF COMMERCE

WASHINGTON, D.C. 20234

10. Project /Ta.sk/Work Unit No.

11. Contract /Grant No.

12. Sponsoring Organization Name and Complete Address (Street, City, State, ZIP)

U.S. Nuclear Regulatory Commission

Washington, D.C. 20555

13. Type of Report & Period Covered

Final

14. Sponsoring Agency Code

15. SUPPLEMENTARY NOTES

16. ABSTRACT (A 200-word or less factual summary of most si^ificant information. If document includes a significant

bibliography or literature survey, mention it here.)

kt the request of the U.S. Nuclear Regulatory Commission (NRC)the National Bureau of

Standards (NBS) has carried out an independent investigation into the question of tornado

Dorne missile speeds, with a view to assisting NRC in identifying pertinent areas of

uncertainty and in estimating credible tornado-borne missile speeds - within the limitations Inherent in the present state of the art. The investigation consists of two parts

L) a study, covered in this report, in which a rational model for the missife motion is

proposed, and numerical experiments are carried out corresponding to various assumptions

on the initial conditions of the missile motion, the structure of the tornado flow, and

the aerodynamic properties of the missile; 2) a theoretical and experimental study of

tornado-borne missile aerodynamics, conducted by Colorado State Univ. (CSU) under contract

tfith NBS, to be covered in a separate report by CSU. In the present report, the factors

affecting missife motion, and their influence upon such motion, are examined. Information

is provided on a computer program developed for calculating missile speeds. Maximum speed

for a number of specified potential tornado-borne missiles are presented, corresponding to

a set of assumptions believed by the writers to be reasonable for design purposes. It is

Dointed out that higher speeds are conceivable if it is assumed that certain circumstances,

examined in the body of the report, will obtain. It is the judgment of the writers that

Lhe probabilities of occurrence of such higher speeds for any given tornado strike are

Low. More than qualitative estimates of such probabilities are, however, beyond the scope

3f this investigation.

~

17. KEY WORDS (six to twelve entries; alphabetical order; capitalize only the first letter of the first key word unless a proper name; separated by semicolons

Missiles; nuclear engineering; structural engineering; tornadoes; wind.

18. AVAILABILITY

^Unlimited 19. SECURITY CLASS

(THIS REPORT)

21. NO. OF PAGES

1 For Official Distribution. Do Not Release to NTIS

UNCL ASSIFIED 62

1

' Order From Sup. of Doc, U.S. Government Printing Office Washington. D.C. 20402. SD Cat. No. CI3

20. SECURITY CLASS

(THIS PAGE)

22. Price

Ix ^ Order From National Technical Information Service (NTIS)

Springfield, Virginia 22151 UNCLASSIFIED $4.50

USCOMM-DC 29042-P74
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