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