RESULTS OF RAMJET FACILITY MODEL TESTS AT MACH 7
Abstract
A test program was conducted to provide ramjet test facility bypass flow second throat diffuser pressure recovery data at a nominal nozzle exit Mach number of 7.0. During the tests a study was made of the effects of stagnation temperature, Reynolds number, ramjet inlet to facility nozzle exit area ratio, and other geometric variables. Two facility models were tested, the earlier Phase I model having a cowl lip angle of 35 degrees with a flare angle of 30 degrees, and the Phase II model having a lip and flare angle of 15 degrees. Prior to the tests it was hoped that it would be possible to attain bypass diffuser pressure recoveries approaching the pressure recovery across a normal shock at the nozzle exit Mach number. The best performance, which was obtained with the Phase II model, gave a pressure recovery corresponding to 65% of normal shock recovery. A significant influence of cowl flare angle was noted since the maximum recovery obtained with the Phase I model was 37% of normal shock recovery.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1963
- Accession Number
- AD0414412
Entities
People
- James L. Grunnet
Organizations
- Arnold Engineering Development Complex