4) An airplane of mass m=5,000 kg is designed to cruise at a velocity of V=234 km/h. It takes off from sea level (Table

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4 An Airplane Of Mass M 5 000 Kg Is Designed To Cruise At A Velocity Of V 234 Km H It Takes Off From Sea Level Table 1 (139.68 KiB) Viewed 9 times

4) An airplane of mass m=5,000 kg is designed to cruise at a velocity of V=234 km/h. It takes off from sea level (Table A-11) and climbs to an altitude of h=4,000 m (Table A-11). The lift and drag coefficients of the wings are shown on the attached chart. The wings have a chord length of c=2 m, a vertical thickness of t=0.1 m, and a total wingspan of b=14 m. Find the following: a. The minimum speed for "safe" take-off (km/h) (5 points) b. The angle of attack to cruise steadily at altitude (°) (5 points) C. The drag for acting on the wings (not fuselage) (5 points) d. The power needed to overcome wing drag (Watts) (5 points) Clark Y airfoil at aspect ratio=6 1.50 .30 CL 1.25- .25 - 1.00 20 .75 ספס ס ס מ ד ר =Fo 2- 15 - Hammon Co .50 10 — N T .25 .05 o 0 -10 -5 0 5 10 15 20 25 30 ANGLE OF ATTACK