Investigations in the Fluid Dynamics of Scramjet Inlets.
Abstract
Research on projects related to the hypersonic fluid mechanics of scramjet inlets is described. Four experimental tasks were performed which used a hypersonic gun tunnel to generate flows having stagnation enthalpies up to 1400K, Mach numbers of about 8.3, and Reynolds numbers for a typical model in the range of 5 to 15 million. The first project investigated the interaction of a shock wave with a laminar boundary layer in the neighborhood of a convex corner. The second project dealt with flow established in a two-dimensional inlet consisting of a forebody-cowl combination. The third project investigated flow in a circular duct having a length to diameter ratio of about 10. The fourth project detailed the effects on inlet performance of using three distinctly different inlet geometries: axisymmetric internal flow, two-dimensional internal flow, and axisymmetric external flow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1992
- Accession Number
- ADA269275
Entities
People
- C. P. Groth
- D. W. Hawken
- J. J. Gottleib
- J. P. Sislian
- K. A. Gordon
- L.-w. Chen
- Philip A. Sullivan
- R. J. Hawboldt
- R. J. Mcgregor
- R. J. Rogers
- R. L. Deschambault
- S. C. Weston
- Sannu Molder
- T. W. Paisley
- Z.-d. He
Organizations
- University of Toronto