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Suppression of cavity-driven flow separation in a simulated mixed compression inlet
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wendt, Bruce J. |
| Copyright Year | 2000 |
| Description | A test facility designed to simulate a bifurcated subsonic diffuser operating within a mixed compression inlet is described. The subsonic diffuser in this facility modeled a bypass cavity feature often used in mixed compression inlets for engine flow matching and normal shock control. A bypass cavity-driven flow separation was seen to occur in the subsonic diffuser without applied flow control. Flow control in the form of vortex generators and/or a partitioned bypass cavity cover plate were used to eliminate this flow separation, providing a 2% increase in area-averaged total pressure recovery, and a 70% reduction in circumferential distortion intensity. |
| File Size | 1317861 |
| File Format | |
| Language | English |
| Publisher Date | 2000-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Boundary Layer Separation Test Facilities Compression Tests Engine Inlets Vortex Generators Supersonic Inlets Inlet Flow Cavity Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
