HIGH SPEED FLOWFIELD ANALYSIS FOR SATELLITE LAUNCH VEHICLE AND REENTRY CAPSULE

摘要

The paper presents numerical and experimental analyses of satellite launch vehicle and reentry capsule at high-speeds. Numerical simulations of free jets emanating from nozzle, impinging of supersonic jets on jet deflector, flowfield over bulbous payload shroud in the transonic and supersonic Mach number range, drag reducing spike attached to blunt body, prediction of angle of attack from the flight data of launch vehicle and depressurization of heat shield during ascent phase of flight. Influences geometrical parameters of various types of reentry capsules on aerodynamic drag are studied at various trajectory points. Results of computational fluid dynamics are compared with the experimental and flight data and exhibit fairly good agreement between them. The reliable estimation of aerodynamic problem associated with launch vehicle can be made in conjunction with computed flow visualizations.