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Experimental aerothermodynamic research of hypersonic aircraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cleary, Joseph W. |
| Copyright Year | 1990 |
| Description | Wind tunnel tests were conducted to establish a benchmark experimental data base for a genetic hypersonic aircraft vehicle. Comprehensive measurements were made at Mach 7 to give flow visualization, surface pressure, surface convective heat transfer, and flow field Pitot pressure for a delta platform all-body vehicle. The tests were conducted in the NASA/Ames 3.5-Foot Hypersonic Wind Tunnel at Reynolds numbers sufficient to give turbulent flow. Comparisons are made of the experimental results with computational solutions of the flow by an upwind parabolized Navier-Stokes code developed at Ames. Good agreement of experiment with solutions by the code is demonstrated. |
| File Size | 643493 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900016638 |
| Archival Resource Key | ark:/13960/t9j43nx92 |
| Language | English |
| Publisher Date | 1990-08-23 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Convective Heat Transfer Turbulent Flow Reynolds Number Hypersonic Wind Tunnels Pressure Data Bases Navier-stokes Equation Hypersonic Speed Research Aircraft Flow Distribution Wind Tunnel Tests Flow Visualization Hypersonic Aircraft Aerothermodynamics Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |