You are working as a flight-test engineer at the Dryden Flight Research Center. During the low-speed phase of the test program for the X-37, you know that the plane is flying at an altitude of 8 km. The pressure at gage 1 is 1550 N/m2, gage; the pressure at gage 2 is -3875 N/m2, gage.
a) If gage 1 is known to be at the stagnation point, what is the velocity of the airplane?
b) What is its Mach number?
c) What is the free-stream dynamic pressure for this test condition?
d) What is the velocity of the air at the edge of the boundary layer at the second point relative to the airplane? What is the velocity relative to the ground? What is the Cp for this gage?