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Interactive calculation procedures for mixed compression inlets
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reshotko, Eli |
| Copyright Year | 1983 |
| Description | The proper design of engine nacelle installations for supersonic aircraft depends on a sophisticated understanding of the interactions between the boundary layers and the bounding external flows. The successful operation of mixed external-internal compression inlets depends significantly on the ability to closely control the operation of the internal compression portion of the inlet. This portion of the inlet is one where compression is achieved by multiple reflection of oblique shock waves and weak compression waves in a converging internal flow passage. However weak these shocks and waves may seem gas-dynamically, they are of sufficient strength to separate a laminar boundary layer and generally even strong enough for separation or incipient separation of the turbulent boundary layers. An understanding was developed of the viscous-inviscid interactions and of the shock wave boundary layer interactions and reflections. |
| File Size | 208778 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900016618 |
| Archival Resource Key | ark:/13960/t88h3fv87 |
| Language | English |
| Publisher Date | 1983-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Internal Flow Laminar Boundary Layer Supersonic Aircraft Oblique Shock Waves Turbulent Boundary Layer Shock Wave Interaction Compression Waves Nacelles Aircraft Design Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
