Answer Happy

Problem 1: Using the dimensional equations of N', A' and M'le (first method), solve the problem below N =- (p.cos @ + 7, sin 0) ds. + COM . (picos LE Ti sin 0) ds CM son (-p, sin 0 + T, cos ) ds. + (p, sin @ + ti cos ) ds LE Consider the supersonic flow over the 2-D rocket at 0° angle of attack. The free stream Mach number is M. =3, and the free stream pressure is Po= 1.01 x 105 N/m². Due to the passage of supersonic flow, oblique shocks and expansion waves formed over the rocket resulting in different values of pressure over multiple parts as shown below. The shear stress is the same over all rocket body of Tw = 431 s-0.2 N/m². The chord length of the rocket is 6 m. Calculate the drag coefficient for the rocket (Note: the upper and lower portions of the rocket are symmetrical about the chord line.) p=4.04 x 10 pa Me=3 Po Pa = 1.01 X 10% pa 2 m P ਬੀ P=5.05 x 10 pa 2 m 3 m 1 m P = 108 x 10 pa Problem 2: Using the dimensional equations of N', A' and M'le (first method), solve the problem below