The pressure coefficient for linearized supersonic flow over an airfoil used to describe the local pressure distribution on the surface of an airfoil when it is operating in a supersonic flow regime. This parameter is particularly relevant when analyzing and designing airfoils for supersonic flight. In supersonic flow, the pressure distribution around an airfoil can vary significantly from that in subsonic flow due to the formation of shockwaves and expansion waves. The pressure coefficient supersonic quantifies these variations and represents the pressure at a specific point on the airfoil’s surface relative to the freestream conditions for supersonic flow.
NOTE: When the surface is inclined into the freestream, hence Cp,B is positive.
- Pressure coefficient at point B (Cp,B)
- Angle between point B on the surface to the freestream (𝜃B) in rad
- Freestream Mach number (M∞)