Accession Number : AD0785605

Title :   Numerical Simulation of Transonic Flow About Airplanes and Helicopter Rotors,

Corporate Author : ARMY AIR MOBILITY RESEARCH AND DEVELOPMENT LAB MOFFETT FIELD CALIF AMES DIRECTORATE

Personal Author(s) : Ballhaus,W. F. ; Caradonna,F. X.

Report Date : 1973

Pagination or Media Count : 16

Abstract : 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)

Descriptors :   *Aerodynamic control surfaces, *Transonic characteristics, Wings, Helicopter rotors, Performance(Engineering), Maneuverability, Shock waves, Flow separation, Mechanical engineering, Computerized simulation, Equations of motion, Costs, Flow fields, Research management

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE