NASA NTRS · 19890037655
A numerical study of hypersonic propulsion/airframe integration problem
Abstract
A numerical analysis procedure useful in the propulsion-airframe integration problem has been established. Flow around a generic hypersonic vehicle forebody is solved using Parabolized Navier-Stokes equations and Thin Layer Navier-Stokes equations. Forebody cross sectional geometry corresponds to a two-ellipse configuration. Effect of forebody geometry on the flow structure, especially at the engine inlet location, is analyzed.
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Narayan, J. R., Kumar, A.. 1989-01-01. A numerical study of hypersonic propulsion/airframe integration problem. https://ntrs.nasa.gov/citations/19890037655
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