Unified Engineering
Spring
Term 2005
Problem P5. (Propulsion)
L.O.Ős C & D
A future high performance military fighter is being designed
with a wing loading (W/S) of 3200 N/m
2.
At a mass of 20,000 kg it must be able to:
1)
fly a 6g combat turn at M=0.7,
2)
accelerate from M=0.8 to M=2.0 in 15 seconds and
3)
fly straight up at M=0.5.
Estimate the maximum design thrust for the engine.
Note, for a 6g turn the load factor, n=6, is the
acceleration perpendicular to the wing.
For n=1, L=W.
Also, assume
all maneuvers occur at an altitude of 11km where the pressure is 22.6 kPa, the
temperature is 217 K, the density is 0.34 kg/m
3, and the speed of
sound is 295 m/s.
Assume the coefficient of lift takes the form
Where
