# Question: an airfoil is in a freestream where 061...

###### Question details

An airfoil is in a freestream where šā = 0.61 atm, šā = 0.819 kg/m3 , and šā = 300 m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assume cp = 1.0045 kJ/kgā K, R = 0.287 kJ/kgā K and š¾ = 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?Ā