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Surface-flow, pressure, and heat-transfer studies on two conical delta wings at a mach number of 6
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Whitehead Jr., A. H. Hefner, J. N. |
| Copyright Year | 1972 |
| Description | An experimental investigation of the surface flow, pressures, and heat transfer on two conical delta wings having attached leading-edge shocks has been conducted at a Mach number of 6. The angle of attack was varied between 0 deg and 12 deg. The pressure data were compared with predictions obtained by the method-of-lines technique, and the heating data were compared with the heating levels predicted by the Spalding-Chi method. |
| File Size | 2957404 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730002541 |
| Archival Resource Key | ark:/13960/t1qg3gc65 |
| Language | English |
| Publisher Date | 1972-12-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics Hypersonic Speed Aerodynamic Configurations Delta Wings Pressure Distribution Wind Tunnel Models Angle of Attack Heat Transfer Aerothermodynamics 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 |