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Low-speed static and dynamic force tests of a generic supersonic cruise fighter configuration
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hahne, David E. |
| Copyright Year | 1989 |
| Description | Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic flight were conducted in the Langley 30- by 60-foot tunnel. The baseline configuration had a 65 deg arrow wing, twin wing mounted vertical tails and a canard. Results showed that control was available up to C sub L,max (maximum lift coefficient) from aerodynamic controls about all axes but control in the pitch and yaw axes decreased rapidly in the post-stall angle-of-attack region. The baseline configuration showed stable lateral-directional characteristics at low angles of attack but directional stability occurred near alpha = 25 deg as the wing shielded the vertical tails. The configuration showed positive effective dihedral throughout the test angle-of-attack range. Forced oscillation tests indicated that the baseline configuration had stable damping characteristics about the lateral-directional axes. |
| File Size | 1747050 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890019115 |
| Archival Resource Key | ark:/13960/t7kq2wz9n |
| Language | English |
| Publisher Date | 1989-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Low Speed Stability Damping Supersonic Cruise Aircraft Research Oscillations Yaw Pitch Inclination Static Tests Aircraft Control Dynamic Tests Aerodynamic Configurations Directional Stability Wind Tunnel Tests Angle of Attack Directional Control Aircraft Configurations Fighter 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 |
