The Effect of Flow Nonuniformities Arising from a Source-Like Hypersonic Nozzle Flow on Two-Dimensional and Axisymmetric Test Bodies,
AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO
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The effect of free stream Mach number gradients on pressures measured on slender, sharp nosed bodies in a hypersonic wind tunnel in investigated. Corrections to the measured surface pressures are obtained using the Mach number gradient as an expansion parameter in a perturbation procedure. The theory is not restricted to very high Mach number flows, nor is it limited to the case where the ratio of the specific heats is very nearly unity. The perturbed flow quantities such as surface pressure perturbation due to the flow nonuniformities are derived as functions of the distances measured along streamlines and normal to the streamlines. The results of wind tunnel measurements are in agreement with the theory.
- Fluid Mechanics