A one dimensional theoretical method for the prediction of the internal performance of a scramjet engine is presented. The effects of changes in vehicle forebody flow parameters and characteristics on predicted thrust for the scramjet engine were evaluated using this method, and results are presented. A theoretical evaluation of the effects of changes in the scramjet engine's internal parameters is also presented. Theoretical internal performance predictions, in terms thrust coefficient and specific impulse, are provided for the scramjet engine for free stream Mach numbers of 5, 6, and 7 free stream dynamic pressure of 23,940 N/sq m forebody surface angles of 4.6 deg to 14.6 deg, and fuel equivalence ratio of 1.0.
Internal Performance Predictions for Langley Scramjet Engine Module
1978
81 pages
Report
Keine Angabe
Englisch
NUMERICAL SIMULATION OF FLOW THROUGH THE LANGLEY PARAMETRIC SCRAMJET ENGINE
SAE Technical Papers | 1989
|The NASA Langley Scramjet Test Complex
AIAA | 1996
|