Numerical Simulation of Transonic Flow About Airplanes and Helicopter Rotors,

Most modern aircraft achieve optimum cruise performance and maneuverability when flying at high subsonic Mach numbers in the transonic regime. As the Mach number increases beyond the optimum, the extent and strength of these shock waves increases, and performance deteriorates rapidly giving way to flow separation and buffet. Predictions of in-flight performance for new configurations are often unreliable. It seems to attempt to use numerical simulations to supplement wind tunnel tests whenever possible. This method is discussed. Modified author abstract