From: clauter@nyx.cs.du.edu (carl lauter)
Subject: Design Project
Organization: Nyx, Public Access Unix @ U. of Denver Math/CS dept.
Date: Mon, 5 Oct 1992 12:35:46 GMT


From clauter@nyx.cs.du.edu (carl lauter)

Hello netters,

        I am currently working on an aircraft design project at
Virginia Tech.  The aircraft we are attempting to design has the
following requirements:
***************************************************************
                         AIAA
           Global Range Transport for Global Mobility

Payload = 800,000 lbs @ 2.5g maneuver load factor

Primary Radius Mission:  Fly 6,500 nm with full payload offload and
return with 15% of full load, without refueling.

Secondary Radius Mission:  Fly 8,000 nm to 12,000 nm with at least
75% payload, land and return empty, without refueling.

Mission Profile:
1.   Warm-up and taxi for 15 min.
2.   Takeoff and climb to best cruise altitude.
3.   Cruise at best altitude and Mach to midpoint.
4.   Descend on course and land.
5.   Taxi/idle for 30 min, offload full payload.
6.   Load 15% of full payload, takeoff and climb to best cruise
     altitude.
7.   Return to best cruise altitude and Mach.
8.   Loiter 15 min (15 min reserve fuel)
9.   Descend, land and taxi 10 min.

Performance:

Initial airfield critical field length = 10,000 ft @ Sea Level
Standard Day.

Midpoint Airfield Critical Field Length less than or equal to
8,000 ft @ 4,000 ft. elevation, 95 F.

The Technology Availability Date is 2010 with a planned Initial
Operational Capability in 2015.

*****************************************************************
We have done a sizing (a combination of Nicolai's method and
Roskam's) of the aircraft and my assumptions and results were:

Aspect Ratio:  7
Mach:  .8
Cruise Altitude:  25,000 ft.
Technology factor (structural):  .8 (80%)
Wing Span:   400 ft.  (too long?)
Wing Area:  22,857 sq ft.
Wing Loading:  207 lbs/ sq ft
Cl max (take - off and landing):  3.7  (too high?)
Thrust per engine:  100,000 lbs  (seem to need 10 engines to take
-
 off)
TSFC:  .45 lbs/lbs/hr
Oswald Efficiency, e:  .95 (95%)
Take - Off run @ SL:  9,968 ft.
Approach Velocity:  128 knots
L/D:   17.59
CDo:  .015 (too low?)


TAKE - OFF GROSS WEIGHT: 4,730,000 lbs.

I am aiming for a cargo floor with dimensions of 160' long by 50'
wide.

Right now we are trying to figure out payload mixes.

We have weights and dimensions for the M1A2, UH-60, AH-64, 463L
pallets.  However, the books we have come across do not have the
dimensions and weights of the various support trucks and other
equipment.

Some vehicles which we do not have on data on are:
The Heavy Expanded Mobility Tactical Truck (HEMTT)
Comanche Helicopter
M113 Family of Vehicles (FOV)
Patriot System
Hawk System
Heavy Equipment Transporter System (HETS)
Palletized Load System (PLS)  <-------------  What type of pallets?

We would appreciate any info you could send me.  We don't have
access to the appropriate Jane's or other books to find this data.



You may have seen my posts this summer on sci.aeronautics
requesting help, before I knew what the project would be.  We need
information on design, engines, hydraulics, air conditioning,
on-board computers, navigation systems, airfoils, etc.  If you or
someone you know can provide this type of information as needed
during the project, please identify yourself with your name, name
of organization, and what component you have information available.

Any information will be greatly appreciated.


Please send all info to clauter@vtssi.vt.edu,  Please do not send
it to my account at nyx.

Thank you in advance,

Carl Espen Lauter