A subscale injector test program conducted with a ten-inch diameter like-doublet injector to determine performance and heat flux profiles vs chamber pressure and propellant mixture ratio, and to determine stability characteristics with various acoustic cavity configurations is described. Results are presented. (Author)
Space Shuttle Maneuvering Engine Reusable Thrust Chamber Program. Task 11: High Epsilon Injector Test Report
1974
52 pages
Report
No indication
English