An inlet-coldpipe assembly was placed in a Mach 0.4 stream to ingest the tip vortex of a forward mounted wing. The strongest vortex was produced by a wing angle of attack of 11 degrees. The vortex displayed a tangential velocity of 57 percent of local stream velocity prior to entering the inlet, and a tangential velocity of 25 percent of local velocity at the simulated comotal-pressure profiles measured by standard compressor-face rakes were changed by the presence of the vortex only at the highest tested inlet mass-flow ratios. (Author)
Preliminary Investigation of Inlet Ingestion of a Wing Tip Vortex
1973
42 pages
Report
No indication
English
Vortex Ingestion in a Diffusing S-Duct Inlet
Online Contents | 1996
|Vortex ingestion in a diffusing S-duct inlet
AIAA | 1996
|