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Aerodynamic characteristics at mach number 0.2 of a wing-body concept for a hypersonic research airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Creel Jr., T. R. Dillon, J. L. |
| Copyright Year | 1978 |
| Description | The static aerodynamic characteristics were studied on a model wing-body concept for a high-speed research airplane in a low-turbulence pressure tunnel. The experiment consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was 0.2 at Reynolds numbers, based on fuselage length, ranging from 2.78 x 1 million to 23 x 2 million. The test angle-of-attack range was approximately -5 to 30 deg at constant angles of sideslip of 0 deg and 4 deg. The elevons were deflected from 5 deg to -15 deg. Roll and yaw control were investigated. |
| File Size | 3297320 |
| Page Count | 49 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780017116 |
| Archival Resource Key | ark:/13960/t1jh8bx6c |
| Language | English |
| Publisher Date | 1978-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Subsonic Speed Aerodynamic Configurations Body-wing Configurations Research Aircraft Wind Tunnel Tests Angle of Attack Aerodynamic Characteristics Hypersonic Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
