Supersonic/hypersonic flowfield predictions over typical finned missile configurations
| Autor: | Bilal A. Bhutta, Clark H. Lewis |
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| Rok vydání: | 1993 |
| Předmět: | |
| Zdroj: | Journal of Spacecraft and Rockets. 30:674-681 |
| ISSN: | 1533-6794 0022-4650 |
| DOI: | 10.2514/3.26372 |
| Popis: | Continuing developments in high-speed finned-missile technology require new accurate and computationally fast numerical techniques for predicting the associated viscous flows at small-to-moderate angles of attack over a wide range of low-to-high Mach numbers (3-15). In this study, a three-dimensional parabolized Navier-Stokes scheme has been developed using a general real-gas flux-vector-splitting technique based on the van Leer approach. Three types of flux-vector-differencing approaches are considered, and their numerical stability and accuracy characteristics are investigated. Results show that a hybrid approach, using first-order full upwinding across the embedded shock and central differencing otherwise, produces an oscillation-free shock front, while it is also strongly convergent and accurate in the near-wall region. This hybrid approach is used to predict Mach 3 and 15 flows over a typical finned-missile configuration at 25,000 ft altitude using perfect-gas and equilibrium-air gas models. Angles of attack of 0, 2, and 5 deg are considered, and fin-thickness and fin-deflection effects are investigated. Fin-deflection studies indicate that, for such high-speed missiles, even small amounts off in deflection can substantially modify the vehicle's aerodynamics. |
| Databáze: | OpenAIRE |
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