ME 437 - Summer 2016 Write your name
Airplane performance and ID
( Introduction )
Follow the organization and format shown
Mass Wing area Altitude Air density
m S h ρ
200 350 6000 0.6604
ton m2 m kg / m
3
Drag polar : CD = CD0 + K CL2 Airspeed
CD0 K V
0.018 0.021 487.50 ( Show V of design point )
km / h
Lift coeff. Drag coeff. Ratio Thurst req. Power req.
CL CD CL / CD T P
0.9258 0.0360 25.717 76.291 10.331
kN MW
Recommended
