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Supersonic experiments on dynamic cross-derivatives due to pitching and yawing of aircraft-like vehicles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Orlik-Ruckemann, K. J. Laberge, J. G. Hanff, E. S. |
| Copyright Year | 1973 |
| Description | A wind tunnel apparatus has been developed and constructed for the determination of moment cross-derivatives due to pitching and yawing on models at moderate angles of attack and sideslip. The apparatus can also be used to determine the direct moment derivatives in pitch and yaw. Experimental results were obtained at Mach 2 on a cone-wing-fin configuration at angles of attack and sideslip up to 15. Although at small values of these angles the cross-derivatives were always negligibly small, measureable effects were sometimes observed, at all angles of attack included in this investigation (i.e. up to 15 deg), when the angle of sideslip was 10 deg or 15 deg. |
| File Size | 2928927 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730022212 |
| Archival Resource Key | ark:/13960/t55f3kp48 |
| Language | English |
| Publisher Date | 1973-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Pitching Moments Yawing Moments Aerodynamic Coefficients Wind Tunnel Apparatus Wind Tunnel Models Angle of Attack Sideslip Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
