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# Consider an airplane flying at a standard altitude of 5 km with a velocity of 270 ms At a point on the wing of the airplane the velocity is 330 m/s Calculate

Consider an airplane flying at a standard altitude of 5 km with a velocity of 270 m/s. At a point on the wing of the airplane the velocity is 330 m/s. Calculate thepressure at this point.

From the problem statement, I know:
Free stream:
v_infinity = 270 m/s
p_infinity = 5.4048*10^4 N/m^2
rho_infnity = 0.73643 kg/m^3
T_infinity = 255.69 K

Wing:
v_wing = 330 m/s

From this, I calculated the speed of sound, and determined that the free-stream mach number was
M_inf = 0.84
And the mach number on the wing was
M_wing = 1.02

Here&#39;s where I get stuck. I tried to apply isentropic relationships

p_wing/p_inf=[1+1/2(gamma-1)M_wing^2](-gamma/(gamma-1))

But that got me a value for the pressure on the wing that was about 50% of p_inf. At this point, I have no idea what else to try.

Apr 27 2020 View more View Less