An airfoil has a sharp leading edge with an included

angle of δ 5 60. It is being tested in a wind tunnel running at

1200 m/s (the air pressure and temperature upstream are 75

kPa and 3.5C). Plot the pressure and temperature in the

region adjacent to the upper surface as functions of angle of

attack, α, ranging from α 5 0to 30. What are the maximum