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Heating augmentation due to compression pad cavities on the project orion cev heat shield
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hollis, Brian R. |
| Copyright Year | 2009 |
| Description | An experimental study has been conducted to assess the effects of compression pad cavities on the aeroheating environment of the Project Orion CEV heat-shield. Testing was conducted in Mach 6 and Mach 10 perfect-gas wind tunnels to obtain heating measurements in and around the compression pads cavities using global phosphor thermography. Data were obtained over a wide range of Reynolds numbers that produced laminar, transitional, and turbulent flow within and downstream of the cavities. The effects of cavity dimensions on boundary-layer transition and heating augmentation levels were studied. Correlations were developed for transition onset and for the average cavity-heating augmentation. |
| File Size | 10898200 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20090024220 |
| Archival Resource Key | ark:/13960/t3cz86g0g |
| Language | English |
| Publisher Date | 2009-06-22 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Correlation Turbulent Flow Wind Tunnels Reynolds Number Augmentation Cavities Hypersonic Speed Compressibility Effects Phosphors Aerodynamic Heating Heat Shielding Boundary Layer Transition Crew Exploration Vehicle Thermography Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
