Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for the transitional flow about two plate configurations at incidence. Both plates are 12 m in length. One has zero thickness, and the other has a thickness of 0.5 m with a nose radius of 0.5 m. The flow conditions simulated are those experienced by the Space Shuttle Orbiter during re-entry at 7.5 km/s. The altitude range considered is that from 200 to 100 km, which encompasses most of the transitional flow regime for the Space Shuttle Orbiter. The DSMC simulations show that transitional effects are evident when compared with free-molecular results for all cases considered. The results demonstrate clearly that the transitional effects are significant even at those altitudes where the flow about a typical space vehicle has often been considered as free molecular. Therefore, it becomes very important to identify these transitional flow effects when making aerodynamic flight measurements of space vehicles as are currently being made with the Space Shuttle Orbiter vehicles. In the absence of calculations, previous flight data analyses have relied exclusively on the adjustments in the gas-surface interaction models without accounting for the transitional effects, which can be comparable in magnitude.
Hypersonic rarefield flow about plates at incidence
Verdünnte Überschallströmung über Platten beim Wiedereintritt
AIAA Journal ; 29 , 8 ; 1250-1258
1991
9 Seiten, 10 Bilder, 4 Tabellen, 21 Quellen
Aufsatz (Zeitschrift)
Englisch
Hypersonic rarefied flow about plates at incidence
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