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