DESIGN OF CONTOURED NOZZLES FOR THE AFAPL 120-INCH SHOCK TUNNEL.
Abstract
The aerodynamic and mechanical designs of hypersonic contoured nozzles for the AFAPL 120-inch, high pressure shock tunnel are described. The nozzles are a multi-Mach number design using throat inserts to vary the exit Mach number. The interchangeable throat inserts extend from the inlet to the nozzle contour inflection point. The desired Mach number range is split into two basic nozzles. The low Mach number range is Mach 8 to 11, and the high Mach number range is Mach 12 to 15. The low Mach number range nozzle has been designed, fabricated, and tested. Only the aerodynamic design of the high Mach number range nozzle has been completed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1968
- Accession Number
- AD0839852
Entities
People
- R. G. Grimm