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NASA NTRS · 19950037643

Interpretation of waverider performance data using computational fluid dynamics

Cockrell, Charles E., Jr.
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Abstract

A computational study was conducted to better understand experimental results obtained from wind-tunnel tests of a Mach 4 conical-flow-derived waverider and a comparative reference configuration, which showed that the aerodynamic performance of the reference configuration was slightly better than that of the waverider. The computational results showed that the predicted surface pressure values and the integrated lift and drag coefficients were much lower for the reference model because the reference model bottom is an expansion surface. However, the lift-drag ratios for the reference model were higher due to a relatively low drag for a comparable amount of lift. The results also showed that the reference model exhibited the same shock attachment characteristics as the conical-flow-derived waverider, and is therefore also a waverider. The shock attachment characteristic gives the waverider a performance advantage over conventional hypersonic vehicles, and the results suggest that altering the bottom surface does not cause significant performance degradation. Flowfield solutions also show that the conical-flow waverider model has better propulsion/airframe integration characteristics than the reference configuration. The results also suggest that generating flowfields other than conical ones may be used to design waveriders with improved aerodynamic performance.

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COMPUTATIONAL FLUID DYNAMICSTRT-THEORETICALMACH NUMBERSHOCK ATTACHMENT

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BibTeXRIS

Cockrell, Charles E., Jr.. 1994-09-01. Interpretation of waverider performance data using computational fluid dynamics. https://ntrs.nasa.gov/citations/19950037643

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