Publisher's Synopsis
Inviscid aerodynamic characteristics of the Space Shuttle Orbiter were computed in support of the Columbia Accident Investigation. The unstructured grid software FELISA was used and computations were done using freestream conditions corresponding to those in the NASA Langley 20-Inch Mach 6 CF4 tunnel test section. The angle of attack was held constant at 40 degrees. The baseline (undamaged) configuration and a large number of damaged configurations of the Orbiter were studied. Most of the computations were done on a half model. However, one set of computations was done using the full-model to study the effect of sideslip. The differences in the aerodynamic coefficients for the damaged and the baseline configurations were computed. Simultaneously with the computation reported here, tests were being done on a scale model of the Orbiter in the 20-Inch Mach 6 CF4 tunnel to measure the deltas . The present computations complemented the CF4 tunnel test, and provided aerodynamic coefficients of the Orbiter as well as its components. Further, they also provided details of the flow field.Prabhu, Ramadas K. and Merski, N. Ronald (Technical Monitor)Langley Research CenterACCIDENT INVESTIGATION; AERODYNAMIC CHARACTERISTICS; INVISCID FLOW; SPACE SHUTTLE ORBITERS; COMPUTATIONAL FLUID DYNAMICS; COLUMBIA (ORBITER); AERODYNAMIC CONFIGURATIONS; DAMAGE; WIND TUNNEL TESTS; METHANE; SIDESLIP; UNSTRUCTURED GRIDS (MATHEMATICS); HYPERSONIC SPEED; COMPUTER PROGRAMS; AERODYNAMIC COEFFICIENTS; ANGLE OF ATTACK; FLOW DISTRIBUTION...
