AERODYNAMIC PECULIARITIES OF FLOW OVER A SPACE VEHICLE AT TRANSONIC AND SUPERSONIC VELOCITIES

摘要

Aerodynamic characteristics of transonic flow over a space vehicle are studied numerically using in-house computational code. Dependencies of axial and normal force coefficients on angle of attack and Mach number are obtained. Nonmonotonic behavior of aerodynamic coefficients is observed with angle of attack increase. Flow patterns are investigated, and characteristics of the separation region are discussed.