Question

1.20 A = 1/2 = 7 1.00 A = = 5 + Problem 2 (25%) An airplane with a mass of 1000 kg flies at 55 m/s in air with a density of 0.9 kg/m3. The wing has an aspect ratio of 5, and has the planform area of 12 m2 a) (10%) Assuming that the wing is the only component that produces lift, calculate the lift coefficient, Cu, in a uniform, horizontal flight. b) (5%) Using the figure, calculate the angle of attack and the coefficient of drag. c) (10%) Calculate the thrust needed for a uniform, horizontal flight. 0.80 G 0.60 0.24 0.40 0.16 3 Ср 0.20 0.08 o 4 12 16 4 8 Angle of attack, a, degrees

Answer 1

Aspect ratio = - Platform Area A= 12 m2 a) Lift Given date Mass on a wooo tog Velocity 55 mile Density (①) Oh bg/m3 Sokation: wefficienti in a uniform and horizontal flights Lift coefficient, (= Alva с 2x55 12 *0.98(85%6 21 lo distame La 06. EL = 0.185 22 -3 b Angle of attack and coefficient of drag? from the graph for aspect ratio zo and tift coefficient G= 0.185 (1) Angle of altack is -3° ; (a) coefficient of diag [6= 0.07 c) Thrust needed: Thrust readed for Loveantal, uniform flight is, F = im Ve + (Poe-Pe) de Poz Pe So (Po-Pe) ke=0 Now, ń = PVA = 0.9x55x 12 = 594 f= rive fan ve = 595x55 = B2670 F = 32Gton Thrust needed a 13267on (Am)