Hi, I need help with this aerospace dynamics question. Please do provide detailed solutions and/or explanations where possible. Thank you.
Question 1 (10 marks) (2022 Paper)
You are working as a flight test engineer at During the low speed phase of the test program for a UAV program, pressure at two locations were measured.
The first pressure is known to be at the stagnation point, and the second is at the edge of the boundary layer above the wing.
You know that the UAV is flying at an altitude of 500 m under the ISA condition. The two pressure readings are:
Point 1: Stagnation Pressure, p1 = 96,920.125 N/m2 Point 2: Static Pressure just outside boundary layer, p2 = 94,454.204 N/m2
Question 1a
Apply the flight test data provided to calculate the velocity of the UAV, and determine the Mach number and the Reynolds Number of the UAV (assume that the characteristic length is 0.2 m and the Dynamic Viscosity is 1.7737 X 10- kg/ms)
Question 1b
Verify the compressibility of the flow over the UAV,and state whether the density can be treated as a constant.
Question 1c
Examine if Bernoulli's equation could be applied to determine the local flow velocity at point 2, and state the reason(s)
Question 1d
Appraise the flow velocity at the point 2
Question le
Appraise the flow around the point 2 to determine the surface pressure on the wing, directly below point 2.
