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Investigation of two bifurcated-duct inlet systems from mach 0 to 2.0 over a wide range of angles of attack
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Latham, E. A. |
| Copyright Year | 1976 |
| Description | A 15.354 percent/scale lightweight fighter type inlet/forebody was tested over a Mach number range of 0 to 2.0. Model configurations consisted of side mounted normal shock and fixed overhead ramp type inlets. Each configuration consisted of two inlets ducted (bifurcated) to supply a single engine face. The normal shock inlet variables included a boundary layer splitter bleed system, alternate boundary layer splitter plates, alternate upper and lower cowl lip shapes, and a blow-in-door (auxiliary inlet) in one lower lip. The only variable of the fixed overhead ramp inlet was the boundary layer bleed flow. Reynolds numbers ranged from 7.6 x 1 million to 19.5 x 1 million/m. Angle of attack ranged from -10 to 35 deg and angle of sideslip from -8 to 8 deg. Test measurements included engine face total pressure recovery, steady state distortion, dynamic distortion, and surface static pressures on the forebody and inlet surfaces. |
| File Size | 3016644 |
| Page Count | 81 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760020078 |
| Archival Resource Key | ark:/13960/t45q9q63x |
| Language | English |
| Publisher Date | 1976-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Flow Distortion Ducted Bodies Wind Tunnel Tests Inlet Flow Aircraft Engines Angle of Attack Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
