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.
Effect of inlet ingestion of a wing tip vortex on turbojet stall margin
1974-09-01
Report
Keine Angabe
Englisch
Stall and surge in turbojet engines
NTRS | 1955
|Stall and surge in turbojet engines
NTRS | 1955
|