This paper highlights the influence of computational methods on design of a wind tunnel experiment which generically models the nozzle/afterbody flow field of the proposed National Aerospace Plane. The rectangular slot nozzle plume flow field is computed using a three-dimensional (3-D), upwind, implicit Navier-Stokes solver. Freestream Mach numbers of 5.3, 7.3, and 10 are investigated. Two-dimensional (2-D) parametric studies of various Mach numbers, pressure ratios, and ramp angles are used to help determine model loads and afterbody ramp angle and length. It was found that the center of pressure on the ramp occurs at nearly the same location for all ramp angles and test conditions computed. Also, to prevent air liquefaction, it is suggested that a helium-air mixture be used as the jet gas for the highest Mach number test case. Three-dimensional calculations of the complete nozzle/afterbody experimental flow field are also performed. The 3-D calculations predict the shape of the jet plume and the flow spillage from the windward side of the model to the expanding plume region. These 3-D results also help to design side fences used to minimize this spillage and help determine optimal locations for probes and other instruments.
Computational design aspects of a NASP nozzle/afterbody experiment
Rechnergestuetzte Entwicklung eines Windkanalversuchs mit Duese und Folgekoerper im Rahmen des National Aerospace Plan (NASP)
AIAA-Papers ; Jan ; 1-16
1989
16 Seiten, 25 Bilder, 1 Tabelle, 13 Quellen
Conference paper
English
Hypersonic Nozzle-Afterbody Experiment: Flowfield Surveys
Online Contents | 1996
|Overview of NASP Nozzle Research
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|Lobed nozzle afterbody research
Tema Archive | 1987
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