Computational inlet-fairing effects and plume characterization on a hypersonic powered model
| Autor: | Lawrence D. Huebner |
|---|---|
| Rok vydání: | 1995 |
| Předmět: | |
| Zdroj: | Journal of Aircraft. 32:1240-1245 |
| ISSN: | 1533-3868 0021-8669 |
| Popis: | A three-dimensio nal computational study has been performed addressing issues related to the wind-tunnel testing of a hypersonic powered-simulation model. The study consisted of two related objectives. The first objective was to determine the three-dimensional flow effects on the aftbody created by fairing over the inlet; this was accomplished by comparing the computational fluid dynamics solutions of two closed-inlet powered configurations with a flowing-inlet powered configuration. Results at four freestream Mach numbers indicate that the exhaust plume tends to isolate the aftbody surface from most forebody flowfield differences, a smooth inlet fairing provides the least aftbody force and moment variation compared to a flowing inlet. The second objective was to predict and understand the three-dimensional characteristic s of exhaust plume development at selected points on a representative flight path of a single-stage-to-orbit vehicle. Results showed a dramatic effect of plume expansion onto the wings as the freestream Mach number and corresponding nozzle pressure ratio are increased. Nomenclature M = Mach number NPR = nozzle pressure ratio, pt,-}ejp*, p = pressure, Pa Re = Reynolds number, 1/m T = temperature, K a = angle of attack, deg AM = Mach number increment, see Figs. 3-5 p = density, kg/m3 Subscripts throat = conditions at the internal nozzle throat t, jet = jet total conditions wall = conditions at a solid wall boundary 00 = freestream conditions |
| Databáze: | OpenAIRE |
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