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Wind-tunnel tests on a 3-dimensional fixed-geometry scramjet inlet at m = 2.30 to 4.60
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Souders, S. W. Trexler, C. A. Mueller, J. N. |
| Copyright Year | 1977 |
| Description | Wind-tunnel tests were conducted on a baseline scramjet inlet model having fixed geometry and swept leading edges at M = 2.30, 2.96, 3.95, and 4.60 in the Langley unitary plan wind tunnel. The unit Reynolds number of the tests was held constant at 6.56 million per meter (2 million per foot). The objectives of the tests were to establish inlet performance and starting characteristics in the lower Mach number range of operation (less than M = 5). Surface pressures obtained on the inlet components are presented, along with the results of the internal flow surveys made at the throat and capture stations of the inlet. Contour plots of the inlet-flow-field parameters such as Mach numbers, pressure recovery, flow capture, local static and total pressure ratios at the survey stations are shown for the test Mach numbers. |
| File Size | 5189257 |
| Page Count | 180 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770013432 |
| Archival Resource Key | ark:/13960/t74v1d581 |
| Language | English |
| Publisher Date | 1977-03-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Fluid Mechanics Pressure Recovery Supersonic Combustion Ramjet Engines Reynolds Number Flow Distribution Wind Tunnel Tests Inlet Nozzles Inlet Flow Leading Edges Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
