(NASA-C~-~.~*.J~~) LP,F,GE-~CALF AD^ hN CED h95-22368 

PFOPr'AN (LA?? PBKPl;al¶ANCE, tCCUSTIC AND 

ULIGkiI BSfIHATICN, JANUhnY, 1SEU (Hamilton 

Standard, Winascr Locks, Cc 6: p unclas 

HC BOU/JF F1d3 LSCL 01~ c~~/L;L 1U752 

NASA Casitractar Report CR.174782 

Large Scaie Advanced Prop-=an (LAB) 

Performance, Acoustic and Weight i 

Estimation L 

Contract NAS 3-23051 

February 1985 
NASA Contractor Report CR-174782 

Large Scale Advanced Prop-Fan (LAP) 

Performance, Acoustic and Weight 

Estimation 

Contract NAS 3.23051 

February 1985 
For sale by the National Technical Information Service, Springfield. Virginia 22161 

NASA€-168 (Rev. 10-75) 

3. Recipient's Catalog No. 

5. Rqmrt Date 

6. Performing Organizatirxl bde 

535-03-12 

13. Worming Organization Report No. 

SP 06A83 

10. Work Unit No. 

11. bnznct or Gnnt No. 

NAS3-23051 

13. Typo of Rapon md Paiod Covued 

Contractor Report 

14. Smnwwing AOmy Cod@ 

1. Rawt No. 

- CR-174782 

2. Gwmm8nt Accuion No. 

4. Title and Subt~tle 

LARGE-SCALE ADVANCED PROPFAN (LAP) 

PERFORMANCE, ACOUSTIC ANIT WEIGHT ESTIMATION 

JANUARY, 1984 

7. Author(s1 

D. Parzych (Acoustic Performance) S. Cohex! (Weight Estimeter) . 

A Shenkman (Aerodynamic Performance) 

9. hfaming Organization Nam and Addra 

Hamilton Standard Division 

United Technologies Corporstion 

P 0. Box 1000 

Wlndsor Loch, Connecticut 06096 

12. Sponsoring Apncy lYIm ad Add*% 

National Aeronautics and Spawe Administration 

Washington, D. C. 20546 

15. Supplrmmtarv Norm 

Project Manager, David A. Sagerser 

Advance Turboprop Project Office 

NASA Lewis Research Center , Cleveland. Ohio 44135 

18. Abmrct 

In comparison to turbo-prap applications, the Prop-Fan is designed to operate in a 

significantly higher range of aircraft flight speeds. Two concerns arise regarding 

operation at very high speeds: aerodynamic performance and noiee generation. 

This data package cwers both topics over a broad range of operating conditfsne for 

the eight (8) bladed SR-TL Prop-Fan. Operating conditions cwered are: Flight 

Mach Number 0 - 0.85; blade tip speed 600-800 it/rec: and cruire pmr load@ 

20-40 SHP/D~. Prop-Fan might and weight scaling estimates are also Included. 

17. Kly Words (Suggmtd by Author(s1 I 

PROP-FAN 

PERFORMA'NCE PREDICTION 

ACOUSTIC PREDICTION 

WEIGHT PREDICTTON 

18. Distribution Sutmnt 

UNCLASSIFIED - UNLIMITED 

19. S8curity aroif. (of this rrpwtl 

UNCLASSIFIED -.*m 

21. NO. of PW 

60 

20. Suuritv Classif. (of this -1 

UNCLASSIFIED 

22. Rice' 
UNDTED 

TECHNOLOGIES 

MAMOLU@W 

STANDARD 

Figure 

1 

2 

3 

4 

5 

6 

7 

8 

9 

10 

11 

12 

ILLUSTRATIONS 

Performance Curve, MN = 0.70 

Performance Curve, MN = 0.75 

Performance Curve, MN = 0.80 

Performance Curve, MN = 0.85 

Reverse Thrust 

Overall Sound Pressure Level, 600 FPS 

Overall Sound Pressure Level, 700 FPS 

Overall Sound Pressure Level, 800 FPS 

Altitude Correction for Tip S eed 

Altitude Correction for SHP/D 4 

Altitude Correction for Near Field Noise 

Directivity as a Function of Tip 

Clearance, MN = 0.60 

Directivity as a unction of Tip 

Clearance, MN = 0.65 

Directivity as a Function of Tip 

'Clearance, MN = 0.70 

Directivity as a Function of Tip 

Clearance, MN = 0.75 

Directivity as a Function of Tip 

Clearance, MN = 0.80 

Directivity as a Function of Tip 

Clearance, MN = 0.85 

Harmonic Spectrum Level, MN = 0.60 

Harmonic Spectrum Levela MN = 0.65 

Harmonic Spectrum Level, MN = 0.70 

Harmonic Spectrum Level, MN = 0.75 

Harmonic Spectrum ~evel, MN = 0.80 

Harmonic Spectrum Level, MN = 0.80 

Harmonic Spectrum Level, MN = 0.85 

Harmonic Spectrum Level, NN = 0.85 

Weight vs Diameter 

TABLES 

Table 

Tabulated Performance, MN = 0.00 

Tabulated Performance, MN = 0.10 

Tabulated Performance, MN = 0.30 

Tabulated Performance, MN = 0.45 

Tabulated Performance, MN = 0.60 

Tabulated Performance, MN = 0.70 

Tabulated Performancel MN = 0.75 

Tabulated Performance, MN = 0.80 

Tabulated Performance, MN = 0.85 

Slipstream Characteristics 

SR7 Far-Field Noise Predictions 

Il f 

Page 

Page 
TABLE OF CONTENTS 

Subject 

INTRODUCTION AND SUMMARY 

PERFORMANCE 

Prop-Fan Performance Estimation 

ACOUSTICS 

WEIGHT 

SR-7L Prop-Fan Near Field Noise Estimation At Cruise 27 

SR-7L Prop-Fan Far Field Noise Estimation 

For Certification 51 

Prop-Fan Weight Estimation 
INTRODUCTION AND SUMMARY 

This data package presents Hamilton Standard's aerodynamic and 

acoustic performance and weight estimates for the 8 bladed SR-7L 

Prop-Fan over a broad range of operating conditions as listed 

below. This Prop-Fan is being designed and fabricated under NASA 

contract NAS3-23051. 

Flight Mach Number 0 - 0.85 

Tip Speed, m/sec ( f t/sec. ) 183 - 244 (600 - 800) 

Cruise Power Loading, ~w/m2 171 - 343 

(sHP/&) 20 - 40 

The design point for the SR-7L is a disc loading of 256.9 ~w/rn~ 

(32 SHP/£~~) relative to diameter at 10,668 meters (35,000 ft) 

ISA and 243.8 m/sec (800 ft/sec) tip speed at 0.80 Mach number. 

Nondimensionally, this represents an advance ratio, J, of 3.06 

and a power coefficient, Cp, of 1.448. The SR-7L has a blade 

activity factor, RF, of 227 and an integrated design lift 

coefficient, CL , of 0.191. 

The aerodynamic performance predictions are based on both theoretical and experimental dat.~~ For the 0.6 - 0.85 Mach number 

range, the HS-H-409 Compressible Vortex method was used. to calculate performance at the design conditions. For off design conditions, performance trends were based on experimental data of the 

8-bladed SR-3 tested in both the NASA LeRC 8' x 6' transonic wind 

tunnel and in the UTRC 8 ft. High Speed Wind Tunnel. For flight 

Mach numbers of 0.55 and below, the HS-H444 Propeller Performance 

Method was used to derive the performance data. This data was 

correlated with the low Mach number data on the SR-3 from the 

UTRC wind tunnel. Recent data on SR-3 indicates that choke 

exists in the blade root area with its associated losses. Alleviation of this choke would improve efficiency at higher MN. 

Subsequent test data will provide us with insight for possible 

subsequent modifications. 

The near field noise estimates are based on Hamilton Standard's 

theoretical calculation procedures HS-F091 which have Seen verified by both acoustic wind tunnel and Jetstar tests. Due to the 

complexity of the far field noise calcula.tions which include the 

effects of ground reflection and tone and duration corrections, a 

graphical procedure is not feasible. Accordingly, a computer 

program which incorporates all of these effects has been developed CSP 06A83F). 

Thus, the aerodynamic and acoustic performance included in this 

ini.tial version of the data package are estimates based on theory 

and test data of a similar Prop-Fan configuration. Following the 

aerodynamic performance and acoustic tests of the aeroelastic 
SR-7A model in the NASA LeRC 8' x 6' and 9' x 15' wind tunnels, 

the aerodynamic and acoustic performance presented herein will be 

revised as dictated by the experimental data. These revisions 

will be published as a supplement to this Data Package. Then, 

when the large scale LAP test program has been completed, this 

entire report will be revised as necessary to reflect any revisions to the weight, ss well as any further modifications to the 

aerodynamic and acoustic performance data. The cost data will 

also be applied at Lhdt tba=. 

The aerodynamic data is presented both as tables (1-9) of nondimensional propeller coefficients and as curves (figures 1-41 of 

net efficiency variation with power loading for several tip 

speeds for a range of Mach numbers. Corresponding slipstream 

characteristic data in terms of average swirl and incremental 

axial induced velocity are presented in tabular form (table 10). 

The reverse thrust data is presented in figure 5. The reverse 

performance estimates were based on SR-3 test data available from 

the UTRC 8s and 18' throat tunnels and the NASA 8 x 6 and 10 x 1C 

tunnels. The estimated maximum negative blade angle for the 

SR-7L is -6' at the 75% radius. The coefficients J, Cp and . 

CT are the same as those used for the positive thrust performance. 

The noise is presented in plots of overall near field noise level 

(free field), altitude correction, directivity changes and harmonic spectrum levels at near field locations. As indicated previously, far field data have not been included in the report. 

However, a computer program has been developed to predict the far 

field noise levels and is available from ~amilton Standard as a 

computer tape. 
UNITED 

TECHNOLOGlES 

MAMOLTOM 

STANDARD 

PERFORMANCE 
PROP-FAN PERFORMANCE ESTIMATION 

This data package provides the SR-7L Prop-Fan Performance in a 

non-dimensional coefficient format which permits the user to estimate performance over a broad range of operating conditions. 

The data is presented in tabular form for ease of computer application. 

The performance is presented in terms of net thrust coefficient 

(CT as a function of power coefficient (Cp) for constant 

NET 

values of advance ratio (J). The following tables are included: 

Mach Number = 0 

Mach Number = 0.1 

Mach Number = 0.3 

Mach Number = 0.45 

Mach Number = 0.60 

Mach Number = 0.70 

Mach Number = 0.75 

Mach Number = 0.80 

Mach Number = 0.85 

Slipstream Characteristics 

The 0.10 to 0.85 Mach number tables also include a tabulation of 

net efficiency (ETA) to allow for a visual estimation ot performance level. 

The non-dimensional coefficients are defined in engineering terms 

as English Units: 

where: -'TNET = Uninstalled Prop-Fan net thrust, pounds 

N = Prop-Fan rotational speed, rpm 

D = Prop-Fan tip diameter, feet 
C 

0 

c, 

z 

C 

u 

. 

m E 

5 a LI LI 

c, 

r: 5 

0 

L, @

a, a,

e 

cn. 

a

c 

la d 

F m 

I 

o

c

9 8 ;$ u 

fi 

LI 

(d

3 a 

0 w 0

I-r aJ P

-rl 4 

Y 4 c

(d m

5 4J FC

LI rn I

a, c a

3 .d O

0 C UL

at, a

II II II 

FI 
Ho = Free stream Mach nai~be~ 

'mi s = Speed of sound, meters per Second 

V = Free stream velocity, meters per second 

4 = Average swirl angle degrees 

AV = Incremental axial induced velocity immediately 

behind disk, meters Ljer second 

where: 

TS = Tip speed, meters per second 

The "Net Thrust (TNET)" is the uninstalled thrust of the PropFan rotor operating in the presence of a nacelle (including spinner). The buoyancy force between the rotor and nacelle face has 

been removed from the rotor thrust and therefore it should not be 

included in the nacelle drag. The uninstalled rotor Prop-Fan 

thrust is for tp& bledes alone. Installed propulsive thrust is 

obtained by addl3g the uninstalled net thrust (TNET) to the 

core engine jet thrust and thea subtracting the drag of the spinner/nacelle and the losses due to nacelle/wing interference. 

The slipstream characteristics are also presented in tabular 

form. Average swirl angle (4) and incremental axial induced 

velocitlr immediately behind the disk over freestream velocity 

(bV/V) are presented as a function of power coefficient (Cp) 

for given values of advance ratio (J). Theoretically the Induced 

axial velocity doubles in the ultimate wake which is 

approximately two diameters downstream. 

The accepted procedure for interpolation of the aerodynamic performance data at conditions not explic$tly specified is as follows : 

a. Calculate the advance ratio, J, utilizing the desired 

Mach number and tip speed (i.e., maintain tip speed constant and 

determine J for varying Mn) . b. Enter Tables 1-9 with the given Mn and constant power coefficient, C ; and the. calculated value of J and determine 

the efficiency an% thrust coefficient. 

The following sample problem utilizes this procedure. The computer program will automatically perform the above interpolation. 
SAMPLE PRORLEN ZI-l .- 

Given: 9 foot diameter Prop-Fan 

2592 SHP 

800 feet per second tip speed 

35,000 feet, ISA, altitude 

0.770 Mach number 

Calculate: Net Thrust 

ND = T.S. x 60/n = 800 x 60/n = 15,278.9 

N = ND/D = 15,278.9/9 = 1697.7 

J = (101.27)(Mo)(C,)/(ND) 

= (101.4)(.770)(576,3)/(15,278.9) 

= 2.94 

Since there is no chart for a 0.770 Mach number, it is necessary 

to interpolate between the available Mach number charts. This is 

done by keeping a constant tip speed. Therefore, the J's are 

ratioed to the Mach numbers. For the given Cp of 1.444: 

M J CT Table 

0.700 2.677 .422 6 

0.750 2.869 .397 7 

0.800 3.060 ,375 8 

0.770 2.945 ,389 Interpolated 

2 Net Thrust = 6605.6(N/lr000) (D/~o)~c /( po/p) 

T~~~ 

= (6605.6)(1.697712( .9)4(.389)/(3.2196) 

= 1510 pounds 

In S.I. Units: 

2592 SHP = 1932.85 Kw 

D = 2.744 meters 

J = (60)(Mo)(Cm/S)/ND 

= (60)(0.770)(296.40)/(1697.7)(2.744) 
C = .389 (from previous solution) 

T~~~ 

= 6721 newtons 

Also for both units: 
TABLE 1. SR-7 PROP-FAN PERFORMANCE 0.00 MACH NUMBER 

J = 0.0 

CP CT ETA 
TABLE 2. SR-7 PROP-FAN PERFORMANCE 0.1 0 MACH NUMBER 

-------- oy30- - - - - - - - - - - - J-= -o .To - - - -- - - - - - - - - - - J = J = 0.50 

C? tT ETA CP CT CP CT ETA . -__ ETA 

. - .- . - . -. .: ' .- - .-* _- _ --.-- 0.0400 0.0237 0.1777 - 0.0213 -0.0002 0.0 - 0.0187-o.oooi - --0.0 

0.0767 0.0907 0.3548 0.0460 0.0442 0.3843 0.0250 0.0030 0.0600 

0.1162 0.1488 0.3842 0.0?93 0.0982 0.4953 0.0540 0.0545 0.5046 

0.1700 0.2210 0.3900 0.12h 0.1647 0.5175 0.0975 0.1111 0.5697 

- 0,2323- ~.3~lb- ,Od??! - - - - , 1.13lL -0.3-375 -0,496-6- - - - - --9-1562_ -Oz182J - 4.5817- - 0.3271 0.3493 0.3570 0.2707 0.3179 0.4697 0.2300 0.2574 0.5596 

0.4295 0.4663 0.3257 0.3634 0.4006 0.4409 0.3193 0.3386 0.5302 

0.5459 0.5408 0.2972 0.4704 0.4757 0.4045 0.4216 0.4190 0.4969 

-- 0.6760 0.6097 0.2706 0.5901 0.5471 0.3709 0.5393 0.4924 0.4565- 

0.8183 0.6715 0.2463 0.7247 0.6142 0.3390 0.6699 0.5622 0.4196 

0.9725 0.7235 0.2232 0.8755 0.6754 0.3086 0.8202 0.6250 0.3810 

1.1509 0.7630 0.1989 1.0481 0.7260 0.2771 0.9860 0.6803 0.3450 

1.3271 0 .'I955 0.1798 1252 - 0.7668- -0 .&VIA- - - - - - & 1zSO- -0 -946 -- 0.3083 - 

-1~9s - 0y8fi9- Xl651- - - - - - 1.*008 0.7988 0.2281 1.3473 0.7624 0.2829 

1.6900 0.816s 0.1443 1.6005 0.8056 0.2013 1.5293 0.7847 0.2566 

1.9026 0.7968 0.12% 1.8265 0.7082 0.1726 1.7685 0.7726 0.2184 

2.0053 0.7781 OZ1l64 2.0053 0.7664 0.1529 2.0055 0.7492 O.1868_ 

0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 

- -cp- - - cT - J - = ,9.60 -- 

- - . . ="-i -- ETA- - .- 0.0187 0.0 0.0 

----. 1.5330 0.0232 0.4213 

0.0613 0.0609 0.5%5- 

0.1170 0.1248 0.6400 
.-At PA= TS 

06 POOR QUALlW 

TABLE 3. SR-7 PROP-FAN PERFORMANCE 0.30 MACH NUMBER 

- - - - - -7x- Tea-- -- - - -- - -- - J-= .2- - - - - -- - - - - - - - - -- - 

J = 1.40 

CP CT ETA tP M ETA CP CT ETA 

J 2 1.60 J = 1.80 

- CP CT EIL CP, eT ETA 

0.0 -0.0123 0.0 0.0 -0.0001 03-- 

0.0969 0.0403 0.6656 0.1958 0.0844 0.7759 

0.2608 0.1274 0.7816 0.3950 0.1770 0.8066 
TABLE 4. SR-7 PROP-FAN PERFORMANCE 0.45 MACH NUMBER 

- - - - - - - - l;no- -- - - - - - - - - J-= - - - - - I - - - - - -. - -- - J = J = 2.00 

CP CT ETA CP CT ETA CP CT ETA 

- - - - - - 7y -Z;2T - - - - - - - - - - - - =-21;140- - - - - - - - - - - - 

J-= -2 .iit - CP CT ETA CP CT ETA CP CT ETA 

-0.0010 -0.0317 0.0 -0.0011 -0.0344 3.0 0.0 -0.0365 0.0 

0.0630 0.0 OS0-. 0.0770 0.0 o.&!- 0.0950 0.0 0.0 

0.1360 0.0fl1 0.5031 0.1680 0.0353 0.5043 o .i380-0~03~6 o .so43 

0.1840 0.0511 0.6044 0.2220 0.0559 0.6043 0.2630 0.0612 0.6050 

------ TrmuCP .CT- ETA 

0.0 -0.016 0.0 

0.1061 -0.0017 0.0 

-0ar0;3987- 

2 # m.6049 

@.S* 0.1Ol5 m.7053 
ORlGMsAL PAGE IS 

OF POOR QUALITY 

TABLE 5. SR-7 PROP-FAN PERFORMANCE 0.60 MACH NUMBER 

- - - - - - *- iroo- - - - - - - - - - - - J.-= -2;iS - - - - - - - - - - - - - - - J * 2.40 

CP CT ETA CP CT ETA CP CT ETA 
ORIGHvAL PAGE rb 

OE POOR QUALITY 

TABLE 6. SR-7 PROP-FAN PERFORMANCE 0.70 MACH NUMBER 

-.-. 

n CT ETA CP CT ETA CP CT ETA 

0.0001 -0.0425 0,O 0.0001 -0.0110 0.0 0.0001 -0.0283 0.0 

- 0.2000 0.0301 0.3913 0.2000 0.0451 0.6UB-JPQP0.3bU5QSL 

3.4000 0.1077 0..7000 0.4000 0.1045 0.7315 0.4000 0.0964 0.7230 

0.6000 0.1807 0.7830 3.6000 0.1722 0.8056 0.6000 0.1567 0.7835 

J = 3.20 J = 3.40 J 3.50 

CP ff ETA CP CT ETA CP CT ETA 

CP ff ETA 

0.0001 -0.0623 0.0 

0.1999 0.0001 0.0019 

TGQdC0.0572 0.5F 

0.6000 0.1126 0.6944 
ORIGHUAL PAGE Ibr 

OF: POOR QUALITY 

SP06A83 

TABLE 7. SR-7 PROP-FAN PERFORMANCE 0.75 MACH NUMBER 

-------- -.----- J = 2.80 

CP CT ETA 0.0001 -0.0335 0.0 

------- ------------------ -- J = 3.00 J = 3.20 

CP CT ETA CP CT ETA 0.0001 -0.0387 0.0 0.0001 -0.0426 0.0 

.P,Z_OO_O 0~0~0~_4155 O.,ZOOe_9AZ25__Q,36O.P 

0.4000 0.0908 0.6810 0.4000 0.0824 0.6592 

0.6000 0.1W 0.7740 0.6000 0.1412 0.7531 

0.8000 0.2120 0.7950 0.8000 0.1993 0.7972 

- LQPPO- 9 1272% - O-SIlZ5 - - - - - 3.QOO-L - Q.2564 - 1.8205- - 

1.2000 0.3248 0.8120 1.2000 0.3076 0.8203 

1.4000 0.3757 0.8051 1.4000 0.3555 0.8126 

J = 3.40 

CT ETA J 3.80 ETA 

J = 4.00 

CP CT ETA -~ooO~~u~l7--6~~ - 

0.1999 -0.0109 0.0 

0.4000 0.0397 0.3970 

0.6000 0.0928 0.6187 

-0 300K - 6;141- 3.7lbC 

1.0000 0.1917 0.7668 

1.2000 0.2397 0.7990 

1.4000 0.2849 0.8140 

l;b0oo--m~~~z0r 

1.8000 0.3651 0.8113 

2.0000 0.3970 0.7940 
OWlGCNAL PAW I%, 

OE POOR QUALITY 

TABLE 8. SR-7 PROP-FAN PERFORMANCE 0.80 MACH NUMBER 

------------------------- J = 3.00 J '- 3.20 

CP CT ETA CP CT ETA 

0.0016 -0.0663 0.0 -0.0027 -0.0656 0.0 

0.2000 0.0073 0.1095 02?OO0 0-0009 0,0144_ 

0.4000 0.0828 0.6210 0.4000 0.0763 0.6104 

0.6000 0.1469 0.7345 0.6000 0.1368 0.7296 

0.7926 0.2047 0.7748 0.8000 0.1941 0.7764 

- WOlO- 0.297L -O,T76Y - - - - - J--OQ.OQ- 9 %2496. - 0,792 - . 1.0014 0.2633 0.7888 1.2016 0.3022 0.8048 

1.2016 0.3174 0.7924 1.4019 0.3518 0.8030 

1.4019 0.3694 0.7905 1.5981 0.4010 0.&030 

. -- - - .- J = 3.40 

ETA 

0.0 

--P.'J ---- 0.5627 

0.7174 

0.7726 

- Qv7987- - 

0.8186 

0.8204 
ORiGlNAL PAGE i.S 

OF POOR QUALITX 

TABLE 9. SR-7 PROP-FAN PERFORMANCE 0.85 MACH NUMBER 

---------------------- J-x-3.Fo - - - - - - - - - - - - - - - 

J a 3.00 J = 3.40 

CP CT ETA 0 CT ETA 0 CT ETA 

0.0 -0.0626 0.0 0 -0.0630 0.0 0.0 -0.0683 0.0 

--- 0.2000 0.0115 0.1725 ~A.ZOOO 0.0090 0,1440 0.2gOO 0.0015 0.0255- 

0.4000 0.0776 0.5820 0.6000 0.0678 O.5b24 0.4000 0.0589 0.5006 

0.60@D 0.1413 0.7065 0.6000 0.1297 0.6917 0.6000 0.1190 0.6743 

0.8000 0.1989 0.7459 O.&OOO 0.1864 0.7456 0.8000 0.1738 0.7% 

- &,oo_oo- 2.~1~ -0~5z - - , -, A-OKOO- -o.A..- - oaw- , , , , J.J-OOL - odqr - o,7~57- - 1.2000 0.3034 0.7585 1.2000 0.2889 0.7704 1.2000 0.2742 0.7769 

1.4000 0.3531 0.7566 1.4000 0.3371 0.7705 1.4000 0.3211. 0.7798 

1.6000 0.3995 0.7691 1.6000 0.S424 0.76- 1.6000 0.3652 0.7760 

- 1.8000 0.4401 0.7335 1.8000 0.4262 0.n77 1.4000 0.4008 0.7722- 

t.aooo 0.4751 0.7126 L.OOOO 0.4~12 0.7379 Z.OOOO 0.~71 0.7601 

t.2000 0.5017. 0.6861 2.2000 o.w.3 o.no3 2.2000 0.7 0.7315 

2.4000 0.5215 0.6519 2.6000 0.5092 0.6789 2.4000 0.4931 0.6986 

- 2-.aooo - ;+p; - z.6~2- - - - - - ~AOO_O - &5232- -0.5452- - - - - - ~.6000- -0.X08z- -0166g5 - 2.8000 0.5808 2.8000 0.5334 0.60% 2.8000 0.5195 0.6308 

3.0000 0.S429 0.5429 1.0000 0.5369 0.5727 1.0000 O.52+9 0.5949 

0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 

J = 3.60 J 8 3.80 J = 4.00 

CP CT ETA 0 CT ETA CC CT €TA 

_ o-o-- -0.0735 0.0 0.0- -0.0622 0.0 b;zoao- -7.m2- -0.c - - - - - - - O.ZOOO- ~l.035~- - 2; - - -. - -7= -- -O:_a63 - 0.0- - - 

0.2000 -0.0117 0.0 

0.4000 0.0529 0.4761 0.4000 0.0447 0.4247 0.4000 0.0366 0.3660 

0.6000 0.1086 0.6516 0.6000 0.0980 0.6207 0.6000 0.0880 0.5867 

-eOOO 0.1613 0.7259 k8000 O.M912,7082 0.8000 0.1378 0.6890- 

1.oooo 0.211~-0;7607 i.oooo 0.1979 0.7520-tSooo-b:iQ~o3404 

1.2000 0.2587 0.7761 1.2000 0.2441 0.Y730 1.2000 0.2301 0.7670 

1.4000 0.3046 0.7833 1.4000 0.2888 0.7839 t.4000 0.2733 0.7809 

1.6000 0.3479 0.7828 1.6000 0.3311 0.1864 1.6000- -0,JlSL - 0,787? - 

-1;boOf - Ern-6- a.7768- - - - - - l?b00b- 3.3?08- -0.7828- - - - - - - 1.8000 0.3538 0.7862 

2.00oo 0.4290 0.7722 2.0000 0.4105 0.77- ~.OOOO 0.3918 0;7836 

2.2000 0.4596 0.7521 2.2000 0.*425 0.7643 2.2000 0.4232 0.7695 

2.4000 0.b801 0.7201 2.6000-0.-$32 O.733b 2.4000 0.~?>.7415 

?%ad6 0.49s? 0.6&6@ 2.6606 0.4783-0.6993 2;&000-6'~05 0.7085- 

2.6000 0.3067 0.6515 2.8000 0.W2 0.6626 2.8000 0.4699 0.4713 

1.0000 0.5131 0.6lS7 3.0000 0.4926 0.6240 3.0000 0.4735 O.bSl1 

- 50- - 2.L - -Oh -, - - -, $0- - 2.2. - -02 - - - - - - 2.L - -02- - 50- - - 

--- - 7--- 

CP CT ETA 0 CI CTA 

O-OSUYO~P;~ 1.8 -O;OTOU-OX-- 

0.2000 -0.0174 0.0 0.2000 -0.0231 0-0 
UNITED 

TECHNOLOGIES 

WOW@M 

mmw 

FIGURE 1. NET EFFlClENCY VS. SHP/D~ AND TIP SPEED 

0.70 MACH NUMBER AT 35,000 FT ISA 

SR-7 PROP-FAN 

18 
UNITED. 

TECHNOLOGIES WOrn@M 

mmw 

FIGURE 2. NET EFFICIENCY VS. SHP/D~ AND TIP SPEED 

0.75 MACH NUMBER AT 35,000 FT ISA 

SR-7 PROP-FAN 
FIGURE 3. NET'EFFICIENCY VS. SHP/D~ AND TIP SPEED 

0.80 MACH NUMBER AT 35,000 FT ISA 

SR-7 PROP-FAN 
UNITED 

TECHNOLOGES 

W0WQM 

mmw 

FIGURE 4. NET EFFICIENCY VS. SHPID~ AND TIP SPEED 

0.85 MACH NUMBER AT 35,000 FT ISA 

SR-7 PROP-FAN 
TABLE 10 

SLIPSTREAM CHARACTERISTICS 
UNITED 

TECHNOWGIES 

MANOLU@M 

SiCAMW 

TABLE 10 (CONTINUED) 

SLIPSTREAM CHARACTERISTICS 
TABLE 10 (CONTINUED) 

SLPSTREAM CHARACTERISTICS 
FIGURE 5. REVERSE THRUST, Cp & -CT VS. J 
ACOUSTIC 
SR-7L PROP-FAN NEAR-FIELD NOISE ESTIMATION AT CRUISE 

The attached noise generalization is for the SR-7L Prop-Fan configuration. It allows estimation of free field overall noise 

level and spectrum level at near-field locations where an aircraft fuselage would be located. Noise can be estimated at forward speeds of 0.6 to 0.85 Mach number, tip speeds from 183-244 

m/sec (600 to 800 ft/sec) at cruise altitudes from 3,088-12,192 m 

(10,000 to 40,000 ft). The levels fore and aft cf the peak noise 

location near the plane of rotation are presented for tip clearances (the distance from the fuselage to the Prop-Fan tip) from 

0.2 to 0.8 Prop-Fan diameters. 

The near-field noise prediction procedure is based on calculations made with the theoretical Prop-Fan prediction procedure developed by Hamilton Standard. The computer results have been 

generalized for the SR-7L Prop-Fan configuration. Acoustic calculations have been referenced to an altitude of 35,000 feet 

(10,668 m). 

Near-field noise generated by a Prop-Fan may be estimated as follows : 

1. Determine the cruise power loading, SHP/D~ (KW/~~), and 

tip speed as described in the aerodynamic performance section. 

2. If the cruise altitude is 10,668 m 135,000 feet), the 

maximum sideline overall sound pressure level at 0.8 diameters 

from the Prop-Fan tips can be determined directly from Figures 6, 

7, and 8. 

If the cruise altitude is other than 1U,668 m (35,000 ft) the actual cruise condition must first be adjusted to the equivalent 

condition at 10,66.8 m (35,000 ft), the noise levels determined as 

above, then corrected to the actual cruise condition. The equivalent condition at 10,668 m (35,000 ft) results in identical 

spanwise lift distribution, angle of attack, and efficiency. 

With equivalent aerodynamic operating conditions, the noise correction is determined from the ratio of acoustic impedance at the 

two altitudes ( pc2). This correction procedure has been 

generalized, and may be accomplished as follows: 

a. Determine the tip speed correction factor, KTS, for 

the actual cruise altitude from Figure 9. Multiply the actual 

tip speed by KTS to obtain an equivalent tip speed for 10,668 m 

(35,000 ft).feet. 

b. Determine the power loading correction factor, KHpt 

for the actual altitude from Figure 10. Multiply the actual 

~w/m~, (SHP/D~) by KH~ to obtain the equivalent ~w/m~ 

(SHP/D~) for 10,668 m (35,000 ft). 
c. The maximum sideline overall sound pressure level at 

0.8 diameters tip clearance for the equivalent operating condition at 10,668 m (35,000 ft) is determined from Figures d, 7, or 

8 at the equivalent tip speed and power loading from a and b. 

d. The maximum sideline noise level from c is adjusted 

from 10,668 m (35,000 ft) to the actual altitude by adding to it 

the AdB noise correction from Figure 11. The adjusted noise 

level is the maximum sideline noise level at the actual altitude 

and operating conditions at 0.8 diameters tip clearance. 

3. If the noise at a measurement point fore or aft of the peak, 

or a tip clearance of other than 0.8 diameters is to be estimated, add the partial levels from Figures 12, 13, 14, 15, 16 or 17 

to the maximum sideline noise level from Step 2. 

4. The spectrum levels relative to the overall sound pressure 

level are shown in Figures 18, 19, 20r 21, 22, 22A and 23 and 23A 

for 0.6, 0.65, 0.7, 0.75, 0.8, and 0.85 cruise Mach numbers 

respectively as a function of tip speed. For altitudes other 

than 10,668 nl (35,000 ft) use the equivalent tip speed defined in 

Step 2a to calculate the spectrum levels. 

In using the attached curves for SH-7L Prop-Fan noise prediction, 

the reader is cautioned that they are only a generalization of 

levels predicted using 'the Hamilton Standard Prop-Fan noise prediction computer program. The noise produced by a Prop-Fan is a 

complex function of configuration variables such as sweep distribution, twist distribution, thickness, and planform, as well as 

operating variables such as cruise Mach number, rotational tip 

speed, and power absorbed. Furthermore, the noise spectrum 

varies with fore and aft distance, and tip clearance. It is obvious then that any data pack will include some simplifying generalizations. The attached data pack information contains some 

of these generalizations. However, the information presented is 

based on theoretical predictions using the SH-7 geometry. The 

information on overall free field noise in Figures 6-8 are plots 

of theoretical predictions at 0.8 diameter tip clearance. The 

spectrum information of Figures 18-23A are plots of theoretical 

predictions for the disc loading, cruise Mach number, altitude, 

and tip speed stated on each figure. If maximum fore and aft 

overall noise levels at 0.8 diameter tip clearance are predicted 

using Figures 6-8, the levels will be the same as those predicted 

using the basic Prop-Fan theory. If noise spectrum information 

1s predicted using Figures 18-23A, the levels will be the same as 

those predicted using the Prop-Fan theory only at (1) the disc 

loading stated on each figure, (2) 0.8 diameter tip clearance and 

(3) the fore and aft location of the peak overall noise level. 

Some degradation from exact theoretical predictions shoula be 

expected when Figures 12-17 are used to adjust for tip clearance 

and fore and aft location and Figures 18-23A are used as spectrum 

levels for conditions and locations other than those stated on 

the figures. 
SAMPLE ESTIMATE OF SH-7L PROP-FAN NEAR-FIELD NOISE 

To assist those using the SH-7L Prop-Fan near-field noise generalization, the following sample calculatian is provided: 

- Disc loading: 256.9 Kw/m2 (32.0 SHp/ft2) 

- Tip Speed: 244 m/sec (800 ft/sec). 

- Cruise Mach Number: 0.8 

- Tip Clearance: 0.4 Diameter 

- Fore and Aft Location: 0.5 Diameter Forward 

- Altitude: 7,620 m (25,000 ft) 

Step 1. The cruise condition is 256.9 Kwjm2 (32.0 SHP/ft2, 

244 m/sec (800 ft/sec), at 7620 m (35,000 ft) altitude. 

Step 2a. At 7620 m (25,000 ft) altitude, the tip speed is given 

as 244 m/sec (800 ft/sec). From Figure 9 at 7620 m (25,000 ft) 

the tip speed correction factor, KTS, is 0.9575. Multiply the 

tip speed at 7620 m (25,000 ft) by 0.9575 to obtain an equivalent 

tip speed of 234 m/sec (766 ft/sec) at 10,668 m (35,000 ft). 

Step 2b. 

is 256.9 

At 7620 m (25,000 ft) altitude the disk power loading 

Kw/m2 (32.0 SHP/~~~). From Figure 8 at 7620 m 

ft) the disk power loading correction factor, KHpr is 

,608. Multiply the disk power loading at 7620 m (25,000 ft) b 

0.608 to obtain an equivalent disk power loading of 161.7 Kw/~ 3 

(19.5 SHP/E~~) at10,668 m (35,000 ft). 

Step 2c. The equivalent operating condition at 10,668 m (35,000 

.ft) is 161.7 ~w/m~ (19.5 sHP/ft2) (Step 2b) at 234 m/sec (766 

ft/sec) tip speed (Step 2a) for a cruise Mach number of 0.8. 

Interpolating between Figures 7 and 8, the maximum sideline 

overall sound pressure level at 0.8 diameters tip clearance for 

the equ,ivalent operating condition at 10,668 m (35,000 ft) is 

143.4 dB. 

Step 2d. From Figure 11 the altitude correction to the maximum 

sideline noise level at 0.8 diameters tip clearance for the 

equivalent operating condition is +4.0 dB. The maximum sideline 

noise.leve1 at 0.8 diameters tip clearance for the actual altitude and operating conditions is 143.4 dB +4.0 dB = 147.4 dB. 

Step 3. For a tip clearance of 0.4 diameter and a fore and aft 

distance of 0.5 diameter forward of the plane of rotation, Figure 

16 indicates that the level from Step 2d should be reduced by 1.8 

dB. The overall sound pressure level at 0.4 diameters tip clearance at 0.5 diameters forward of the plane of rotation for 7620 m 

(25,000 ft) altitude, 256.9 Kw/m2 (32.0 SHP/~~~), 244 m/sec 

(800 ft/sec) and 0.8 cruise Mach number is 147.4 dB - 18 dB = 

129.4 dB. 
Step 4. The spectrum levels are determined by adding the spectrum level corrections for the equivalent tip speed of 234 m/sec 

(766 ft/sec) interpolated from Figure 22 to the overall noise 

level from Step 3 as tabulated below: 

Level Relative to Sound Pressure Level 

Blade Passage Overall Sound of Blade Passage 

Frequency Pressure Level Frequency Harmonics 

( BPF 

2 x BPF 

3 X BPF 

4 x UPF 

5 x BPF 

6 x BPF 

7 x BPF 

8 x BPF 

9 x BPF 

10 x BPF 
roo Pn (1 a3 MIS) TIC SPEED 

38,000 FT (1 0,568M) ALTITUDE 

FIGURE 6. PEAK OVERALL FREE FIELD NOISE LEVELS 

;AT 0.8 DIAMETERS BLADE TIP CLEARANCE 
7qn pPS ((21 3.5 M/S) TIP SPEED 

35,000 FT (I Os66IM) ALTITUDE 

40 

FIGURE 7. PEAK OVERALL FREE FIELD NOISE LEVELS AT 

0.8 DIAMETERS BLADE TIP CLEARANCE 
FIGURE 8. PEAK OVERALL FREE FIELD NOISE LEVELS 

AT 0.8 DIAMETERS BLADE TIP CLEARANCE 
UNnU) 

TECHNOLOGIES ,,,-,,-- ;.- r7, < 

W' la !lY J&L el$!! ' "- v UAJ~&&&~ 

CORRECTION FOR THE EFFECT OF ALTITUDE ON TIP ROTATIONAL 

SPEED AT CONSTANT ADVANCE RATIO, .I, AND CONSTANT FLIGHT 

MACH NUMBER 

. . 

I I I I I I I I 

3000 4000 SO00 a000 7000 8000 

Id 

9000 10,000 11,000 12.000 

M 

ALTITUDE 

FIGURE 9 
CORRECTION FOR THE INFLU~CE OF ALTITUDE ON SHP/D~ AT 

CONSTANT POWER COEFFICIENT. CP, CONSTANT ADVANCE RATIO, 

J. AND CONSTANT FLIGHT MACH NUMBER 

I .4 

1.2 

1 .o 

I 

Y 

a 

0 

0.8 

< 

0 

z 

2 

U 

U 

a 

a 

0 0.8 

U 

u 

0 

% 

t 

m 

0.4 

--* 4-. . . -+--.+. - - 

0.2 

0 

10,000 15.000 20.000 21.000 30.000 35.000 40.00 

FT 

I ! I I I I I I I I 

SO00 4000 5000 8000 7000 8000 ,000 10,000 11.000 12.000 

M 

ALTITUDE 

FIGURE 10 

3 5 
CORRECTION FOR THE INFLUEN- OF ALTITUDE ON NEAR FIELD 

CRUISE NOISE LEVEL AT CONSTANT POWER COEFFICIENT, CP, 

CONSTANT ADVANCE RATIO, J, AND CONSTANT FLIGHT MACH NUMBER 

FIGURE 11 
-0.5 

AFT 

CORE AND ACT LOCATIONS IN FAN DIAMETERS 

FIGURE 12. DIRECTIVITY AS A FUNCTION OF TIP CLEARANCE 0.6 MN 
FORWARD AFT 

FORE AND AFT LOCATIONS IN CAN DIAMETERS 

FIGURE 13. DIRECTIVITY AS A FUNCTION OF TIP CLEARANCE 0.65 MN 
UNITED 

TECHNOUXilES 

WW@M 

gq" 

FORWARD ACT 

FORE AND AFT LOCATIONS IN FAN DIAMETERS 

FIGURE 14. DIRECTIVITY AS A FUNCTION OF TIP CLEARANCE 0.7 MN 

OVERALL SOUND PRESSURE LEVEL IN dB WITH RESPECT TO O.8D MAX SIDELIN
FORWARD AFT 

FORE AND APT LOCATIONS IN FAN DIAMETERS 

FIGURE 17. DIRECTIVITY AS A FUNCTION OF TIP CLEARANCE 0.85 MN 
FIGURE 18. LEVEL OF BLADE PASSAGE FREQUENCY HARMONICS RELATIVE 

TO OVERALL SOUND PRESSURE LEVELS 

0.6 MN, 0.8 DIAMETER TIP CLEARANCE, 35,000 FT (10.668M) 
BLADE PASSAGE FREQUENCY HARMONIC 

FIGURE 19. LEVEL OF BLADE PASSAGE FREQUENCY HARMONICS RELATIVE 

TO OVERALL SOUND PRESSURE LEVELS 

0.65 MN, 0.8 DIAMETER TIP CLEARANCE. 35,000 FT (10.668M) 
-80 

1 2 3 A s 6 7 8 9 10 

BLADE PASSAGE FREQUENCY HARMONIC 

20. LEVEL OF BLADE PASSAGE FREQUENCY HARMONICS RELATIV 

TO OVERALL SOUND PRESSURE LEVEL 

0.7 MN. 0.8 DIAMETER TIP CLEARANCE. 35,000 FT (10,668M) 

45 
FIGURE 21. LEVEL OF BLADE PASSAGE FREQUENCY HARMONICS RELATIVE 

TO OVERALL SOUND PRESSURE LEVEL 

0.75 MN, 0.8 DIAMETER TIP CLEARANCE, 35,600 FT (10,668M) 
FIGURE 22. LEVEL OF BLADE PASSAGE FREQUENCY HARMONICS RELATIVE 

TO OVERALL SOUND PRESSURE LEVEL 

0.8 MN, 0.8 DIAMETER TIP CLEARANCE. 35,000 FT (1 0,668M) 
FIGURE 22A. LEVEL OF BLADE PASSAGE FREQUENCY HARMONIC RELATIVE TO 

OVERALL SOUND PRESSURE LEVELS 

0.8 MN, 0.8 DIAMETER TIP CLEARANCE, 35,000 FT (10,668M) 
UNITED 

TECHNOLOGIES 

GIMULU@M miBL.ADE PASSAGE FREQUENCY HARMONIC 

FIGURE 23. LEVEL OF BLADE PASSAGE FREQUENCY HARMONIC RELATIVE 

TO OVERALL SOUND PRESSURE LEVELS 

0.85 MN, 0.8 DIAMETER TIP CLEARANCE, 35,000 FT (10,668M) 
UNITED 

TECHNOLOGIES 

WULUQM mAMw 

FIGURE 23A. LEVEL OF BLADE PASSAGE FREQUENCY HARMONIC RELATIVE 

TO OVERALL SOUND PRESSURE LEVELS 

0.85 MN, 0.8 DIAMETER TIP CLEARANCE, 35,000 FT (10,668M) 
SR-7L PROP-FAN FARLFIELD NOISE ESTIMATION FOR NOISE CERTIFICATION 

Estimation of SR-7L Prop-Fan noise in the far-field is more complicated than estimation of noise in the near-field due to additional conside~ations, such as atmospheric attentuation and 

ground reflect..on effects. In addition, noise certification limits are in terms of-Effective Perceived Noise Level (EPNL) which 

includes tone and duration corrections. These are dependent on 

the spectrum characteristics as well as flight speed and altitude 

over the measuring microphone. It is thus not practical to devise simple graphical procedures to provide reasonable estimates 

of Prop-Fan EPNL. 

In place of a graphical procedure, Hamilton Standard has developed a FORTRAN computer program SP06A8'F which will calculate the 

EPNL of the SR-7L Prop-Fan during take-off and approach. This 

.program.includes all the currently known components of Prop-Fan 

noise which are significant during low flight speed operation. 

In addition, the computer program will calculate ground reflection effects, so that noise estimates representative of that 

which would be measured for noise certification, with a microphone located over a ground plane, can be made. Finally, the 

computer program has provision for inputing engine noise, so that 

the noise of a complete full scale propulsor can be estimated. 

Table XI presents sample representative takeoff and approach 

noise levels as calculated by SP 06A83F. These calculaions were 

made for Prop-Fan noise only, and do not include any engine noise. 
TABLE XI. SR7 FAR-FIELD NOISE PREDICTIONS 

(SP 06A83F Sample Calculation) 

(For 2-Engine Aircraft 13.9 Foot Diameter Prop-Fans) 

Aircraft 

Height EPNL 

Tip Above EPNL 4 ft FAR-36 

- SHP Speed Ground Free- Micro- Stage-3 

Conditions (fps) (ft) Field phone Limit 

Cut-Back 41.6 700 2750 75.4 80.3 89.9 

Power 

Take-of f 

(0.20E.IN) 

Approach 16.8 650 394 79.3. 81.8 99.5 

(0.20MN) 
WEIGHT 
PROP-FAN WEIGHT ESTIMATION 

Data package SP 06A83 reflects Hamilton Standards most recent 

estimates for Prop-Fans. The technology time frame chosen is 

1987 which means that a technology freeze occurs in that year, 

and a production development program initiated then would incorporate the technology level reflected by these weight estimates. 

Weight relationships were generated for a Prop-Fan with both 

eight (8) and ten (101, 180AF blades with 1987 technology incorporated. These relationships are represented by curves A and B 

of Figure 24. A weight relationship was also generated for the 

current technology LAP with a 230AF blade configuratioc and an 

advanced pitch change system. This is represented by curve C of 

Figure 24. For comparison purposes, both the LAP configuration 

and the equivalent sol'dity, 1987 technology Prop-Fan configuration are depicted. 

Curves A & B of Figure 24 provide uninstalled 1987 technology 

rotor weight estimates. These weights are consistent with data 

package SP 06A82. The weights assure a blade technology with advanced airfoils, a hollow titanium spar, 8 lb density foam fill, 

a fiberglass shell, and a titanium sheath; a steel disc; a 4750 

psi advanced technology pitch change system with onboard power 

for ice protection; and a fiberglass spinner. 

The power loading, (sHP/D~), term u~zd on the rotor weight 

curve in Figure 24 is based on the maximum power delivered to the 

rotor. The tip speed, (T.S.), that should be used for rotor 

weights is the maximum at which the rotor normally operates. The 

weight curve in Figure 24 is plotted for a tip speed of 800 

ft/sec and a power loading of 70 Hp/ft2. Rotor weights for 

other tip speeds and power loadings can be obtained by utilizing 

the conversion formulae provided on the curve notes. 
i, I987 TECHNOLOG I!." I . ',', 

.WEIGHT INCLUDES: 

BLADES, HUB. RETENTION. 

ACTUATOR. CONTROL. 

SPINNER. DEICING 

.WT. AT ALL OTHER VALUES 

OC 73.. WT.n 

0.3 

.WT. AT ALL OTHER VALUES 

OF SHPID'. wrsmr 

WTWW= wm[ %!!E!]o-~ 70 

NOTES 

@PROP. FAN DESIGN WITH 

LAP BLADE AND ADVANCED 

PITCH CHANGE MECHANISM 

@PROP. CAN DESIGN WITH 

PDVANCOD TECHNOLOGY 

FOR THE SAME TOTAL 

SOLIDITY AS LAP 

FIGURE 24. PROP-FAN WEIGHT VS. DIAMETER 
SAMPLE WEIGHT CALCULATION 

GIVEN: Diameter, D = 13 ft. 

Max. operating horsepower to the Prop-Fan = 10985 

8 blades 

CALCULATE: SHP = 10985 = 65.0 

D~ (1312 

Rotor weight from Figure 24 for - SHP = 70 nnd 

D2 . 

T.S. = 800 ft./sec. is 1160 pounds 

Correcting weight for - SHP = 65.0 

~2 

WT65 = 1160 Mo3 65 = 1134 ibs. 

Correcting weight for T.S. = 700 ft./sec. 

WT700 = 1134 Idoo3 700 = 1089 lbs. 

Therefore the rotor weight for the above 

condition is 1089 lbs.