Half Model Restrictions for Linear Plug Nozzle Testing
| Autor: | W. J. Bannink, Menko Wisse |
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| Rok vydání: | 2001 |
| Předmět: | |
| Zdroj: | AIAA Journal. 39:2148-2157 |
| ISSN: | 1533-385X 0001-1452 |
| Popis: | Linearplugnozzleshavebeen receivingmoreattention sincethedevelopment ofthesinglestageto orbitreusable launch vehicle. To clarify the fundamental features of linear plug nozzle e ow, experiments have been performed with half models because the design of the plug nozzle is symmetric. Experimental and numerical results are presented to investigate the usefulness of a half model design. The experiments were conducted on a half model without external e ow and with an external e ow at a Mach number of M1 =2. The results have been used to validate computations using Navier ‐Stokes equations provided with a Baldwin ‐Lomax turbulence model and a Degani‐Schiff correction. For comparison computations were performed for a full model subjected to the same conditions. For all of these conditions, the effects of increasing or decreasing pressure ratio have been taken into account. Nomenclature A = area A ¤ = sonic area CD = drag coefe cient CF = thrust coefe cient E = thrust coefe cient error F = thrust L = full plug length M = Mach number p = pressure T = temperature X, Y, Z = coordinates ° = ratio of specie c heats µt = tilt angle of the throat Subscripts c = chamber conditions d = design conditions e = exit nb = nozzle base nr = nozzle ramp t = throat t = stagnation conditions vb = vehicle base 1 = freestream conditions |
| Databáze: | OpenAIRE |
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