Numerical Modeling of the Effect of Geometric Asymmetry on the Damping Aerodynamic Characteristics of Supersonic Sectional Flight Vehicles

摘要

A method for calculating the steady inviscid supersonic flow past equivalent bodies is applied to the analysis of the time-dependent aerodynamic characteristics of sectional flight vehicles with an asymmetric rear stabilizer. The stabilizer asymmetry can be caused by either its deflection or a change in its shape due to heat-shield coating removal, boundary layer displacement thickness, developed separation flow zones, local deformations, or other distortions in the baseline form. A mathematical apparatus for modeling asymmetric sectional configurations by means of ruled surfaces with arbitrary contours of the reference cross-sections is developed. The uniform perfect-gas Moo = 6 flow past sectional vehicles performing plane oscillations about the zero angle of attack is calculated (the adiabatic exponent γ=1.4). The calculated results demonstrate the effect of various asymmetries in the body shape on the aerodynamic coefficients.