A two-dimensional inlet and a turbojet engine were investigated in a Mach 0.4 stream so as to ingest the tip vortex of a forward mounted wing. Results show that ingestion of a wing tip vortex by a turbojet engine can cause a large reduction in engine stall margin. The loss in stall compressor pressure ratio was primarily dependent on vortex location and rotational direction and not on total-pressure variations across the compressor face. (Author)
Effect of Inlet Ingestion of a Wing Tip Vortex on Turbojet Stall Margin
1974
57 pages
Report
Keine Angabe
Englisch