Navier-Stokes simulations of Orbiter aerodynamic characteristics including pitch trim and bodyflap

摘要: An analysis of the longitudinal aerodynamics Shuttle Orbiter in hypersonic flight regime is made through use computational fluid dynamics. Particular attention given to establishing cause "pitching moment anomaly," which occurred on Orbiter's first flight, and computing a complete configuration at conditions. Data from ground-based facilities as well data are used validate computed results. Analysis shows that pitching anomaly real-gas chemistry effect was not simulated facilities, air test gas. Computed for within 5% measured values trim bodyflap deflections predicted 10%.