Consider an infinitely thin flat plate of chord c at an angle of attack α in a supersonic flow. The pressure distribution

can be approximated as follows:

i) Upper surface: Cp constant at -0.8 from the leading edge to 60% chord, then increasing linearly to +0.1 at the trailing edge.

ii) Lower surface: Cp constant at –0.4 from the leading edge to 60% chord, then increasing linearly to +0.1 at the trailing edge.

Estimate the lift coefficient and the pitching moment coefficient about the leading edge due to lift.