On the Shock Stand-Off Distance in an Inviscid Hypersonic Source Flow Past Two-Dimensional Bluff Bodies
Abstract
The effect of high Mach number flows on test bodies can be estimated reasonably well by using the Newtonian approximation. If the flow is like a source flow then the effects of the ambient flow gradients on the flow parameters in the shock layer can be obtained by modifying the Newtonian formula. Freeman's theory is adopted in the present study and changes in surface pressure and shock detachment distance of a two-dimensional blunt body are obtained by using a perturbation scheme. Based on the ratio of the axial distance of a station on the body from the nose (which is the origin of the coordinate frame) to the distance of the source location from the origin as a perturbation parameter, first order corrections to the surface pressure and the shock detachment distance are derived.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1971
- Accession Number
- AD0740566
Entities
People
- K. S. Nagaraja
Organizations
- Air Force Research Laboratory