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Self stabilizing sonic inlet
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1979 |
| Description | An inlet suitable for a turbine engine in a STOL, VTOL or CTOL aircraft is described. A circumferentially extended slot is provided in the inner surface of the air inlet at the windward side and downstream of the throat region. The slot communicates with a circumferential plenum chamber formed in the front of the air inlet just behind the lip. Circumferentially extending rows of apertures are provided on the lip establishing two sets of apertures spaced circumferentially away from the slot in opposite directions. The slot removes the boundary layer from the critical portion of the diffuser to minimize or eliminate flow pressure loss or separations resulting from diffusion or tuning. The apertures are in a region of low static pressure on the lip of the inlet and serve as a source of suction to cause air flow into the slot. |
| File Size | 414727 |
| Page Count | 5 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790016805 |
| Archival Resource Key | ark:/13960/t24b7w79x |
| Language | English |
| Publisher Date | 1979-05-15 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Boundary Layer Separation Air Intakes Subsonic Speed Engine Inlets Apertures Inlet Flow Short Takeoff Aircraft Turbine Engines Boundary Layer Flow Vertical Takeoff Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
