Question: an airfoil is in a freestream where 061...
An airfoil is in a freestream where 𝑝∞ = 0.61 atm, 𝜌∞ = 0.819 kg/m3 , and 𝑉∞ = 300 m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assume cp = 1.0045 kJ/kg⋅K, R = 0.287 kJ/kg⋅K and 𝛾 = 1.4.
a. Calculate the velocity at that point? List the assumptions you have made?
b. Calculate the error if you assume that the flow is incompressible?