UNSTEADY AERODYNAMIC FLOW FIELD ANALYSIS OF THE SPACE SHUTTLE CONFIGURATION Part I:ORBITER AERODYNAMICS

摘要

An analysis of the steady and imsteady aerodynamics of the space shuttle orblter has been performed. It is shown that slender wing theory cam be modified to account for the effect of Mach number and leading edge roundness on both attached and separated flow loads. The orbiter unsteady aerodynamics can be computed by defining two equivalent slender wings, one for attached flow loads end another for the vortrekinduced loads. It is found that the orbiter is in the transonic speed region subject to vortex-shock-boundary layer interactions that cause highly nonlinear or discontinuous load changes which can endanger the structural integrity of the orbiter wing and possibly cause snap roll problems. It is presently impossible to simulate these interactions in a wind tunnel test even in the static case. Thus, a well planned combined analytic and experimental approach is needed to solve the problem.