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Configuration heating for a hypersonic research airplane concept having a 70 deg swept double-delta wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lawing, P. L. |
| Copyright Year | 1978 |
| Description | The heating on a candidate hypersonic research airplane configuration has been examined experimentally at Mach 6 by the phase-change-paint technique. The configuration has a double-delta wing with tip fins. Phase-change-paint diagrams give heating data for the model top, side, and bottom, with and without deflected elevons for an angle-of-attack range of 0 deg to 24 deg. Nominal Reynolds numbers are on the order of 15,000,000 with supplementary data at length Reynolds number of 4,000,000, which moves the model from the predominantly turbulent into the predominantly laminar regime. Also, intermediate Reynolds numbers were investigated on the lee side for one angle of attack. |
| File Size | 2640831 |
| Page Count | 77 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780015446 |
| Archival Resource Key | ark:/13960/t02z61h9t |
| Language | English |
| Publisher Date | 1978-05-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Heating Research Aircraft Delta Wings Aircraft Configurations Heat Transfer Coefficients Heat Transfer Hypersonic Vehicles 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 |
