THE PERFORMANCE OF A SHOCK TUBE MODIFIED FOR USE IN RAMJET INLET INVESTIGATIONS.
Abstract
A reduced-width test section containing Mach 4, convergent-divergent nozzle blocks was attached to a shock tube. Mach number and flow steadiness measurements were made in the test section. A ramjet inlet model was installed in the test section. Flow field Schlieren pictures were recorded using still and high-speed motion picture photography. This study demonstrated the feasibility of using the shock tube for ramjet inlet studies. Comparison of theoretical flow patterns with the flow patterns over the inlet model showed close agreement except for distortion due to the boundary layer on the walls of the tube. The boundary layer, more than 1/8 inch thick, made the test section unsuitable for quantitative measurements of the flow patterns. The reduced width of the test section improved the quality of the Schlieren pictures and the test flow times obtained in previous studies (AD-292 180 and AD-419 597). Steady flows of average Mach number 3.05 were obtained for 20 milliseconds. Test flow time was a function of shock strength, while the test section Mach number and flow steadiness appeared to be independent of shock strength. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1964
- Accession Number
- AD0610175
Entities
People
- Terence Joseph O'rourke
Organizations
- Air Force Institute of Technology