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Low-speed aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept delta wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Creel Jr., T. R. Penland, J. A. |
| Copyright Year | 1974 |
| Description | An experimental investigation of the low-speed static longitudinal, lateral and directional stability characteristics of a hypersonic research airplane concept having a 70 deg swept delta wing was conducted in a low-speed tunnel with a 12-foot (3.66 meter) octagonal test section. Aircraft component variations included: (1) fuselage shape modifications, (2) tip fins, (3) center vertical fin, (4) wing camber, and (5) wing planform. This investigation was conducted at a dynamic pressure of 262.4 Pa (5.48 psf), a Mach number of 0.06, and a Reynolds number of 2.24 million, based on body length. Tests were conducted through an angle-of-attack range of 0 deg to 30 deg with elevon deflections from +5.0 deg to minus 30.0 deg. The complete configuration exhibited positive static longitudinal, lateral and directional stability up to angles of attack of at least 20 deg and was trimmable to lift coefficients of at least 0.70 with elevon deflections of minus 30 deg. |
| File Size | 2088312 |
| Page Count | 78 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740023372 |
| Archival Resource Key | ark:/13960/t7tn20g0r |
| Language | English |
| Publisher Date | 1974-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Aerodynamic Configurations Research Aircraft Delta Wings Wind Tunnel Stability Tests Wind Tunnel Models Aerodynamic Stability Hypersonic Aircraft Stability Derivatives Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
