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The effect of asymmetric attack on trim angle of attack
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Kruse, R. L. |
| Copyright Year | 1983 |
| Description | Ballistic range tests were conducted to determine the effect of an asymmetrically ablated heat shield on the trim angle of attack of an entry vehicle. The tests, which were in support of Project Galileo, were conducted in atmospheric air at Mach numbers from 0.7 to 2.0. For the results for the configuration that was tested, the deduced trim angle varied between 13 deg and 21 deg. |
| File Size | 17640543 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830016202 |
| Archival Resource Key | ark:/13960/t3033pc4x |
| Language | English |
| Publisher Date | 1983-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Ablative Nose Cones Aerodynamic Balance Galileo Project Ballistic Ranges Heat Shielding Angle of Attack Atmospheric Entry Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |