The differences revealed by initial space flights between preflight aerodynamic predictions and actual flight data, were investigated. For the Space Shuttle these differences were notable for longitudinal trim during high speed reentry. To investigate these differences, several computer codes were applied to a modified Space Shuttle Orbiter to determine aerodynamic parameters over a wide range of conditions. Computations were carried out for wind tunnel conditions and flight conditions to assess Mach number, real gas, and viscous effects on the reentry aerodynamics of the orbiter. Based on the computational fluid dynamics results and a semiempirical analysis of viscous effects, an aerodynamic model for the orbiter was developed to extrapolate wind tunnel data for the Space Shuttle Orbiter to flight conditions.


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