HYPERSONIC CYLINDER WAKE STUDIES AT MACH 20
Abstract
The fluid mechanical behavior of wakes behind simple bodies is described. Experimental measurements in both the viscous and the inviscid flowfields of a two-dimensional circular-cylinder model were made in the LMSC hot-shot tunnel. The free-stream Reynolds number, based on model diameter, was varied between 1,800 and 90,000 at a nominal Mach number of 20. Profiles of pitot pressure, which extended from the axis to the bow shock wave, were measured at four locations behind the model. Schlieren photographs of the bow and wake shock waves were taken. Calculations of the inviscid flow-field over the model were made by means of a method-of-characteristics program for comparison with experimental data. An embedded shock wave was inserted numerically in the flow field to simulate the wake shock-wave system. The measured and computed profiles of pitot pressure in the inviscid regions of flow, as well as shock-wave shapes, are in good agreement. Details of the pitot-pressure distribution in the viscous wake are evident in the experimental data.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1963
- Accession Number
- AD0435740
Entities
People
- Adam Brown
- C. Smith
- R. L. Kramer
Organizations
- Lockheed Martin Missiles and Space