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Application of wind tunnel free-flight technique for wake vortex encounters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jordan Jr., Frank L. Brandon, Jay M. Buttrill, Catherine W. Stuever, Robert A. |
| Copyright Year | 1997 |
| Description | A wind tunnel investigation was conducted in the Langley 30- by 60-Foot Tunnel to assess the free-flight test technique as a tool in research on wake vortex encounters. A typical 17.5-percent scale business-class jet airplane model was flown behind a stationary wing mounted in the forward portion of the wind tunnel test section. The span ratio (model span-generating wingspan) was 0.75. The wing angle of attack could be adjusted to produce a vortex of desired strength. The test airplane model was successfully flown in the vortex and through the vortex for a range of vortex strengths. Data obtained included the model airplane body axis accelerations, angular rates, attitudes, and control positions as a function of vortex strength and relative position. Pilot comments and video records were also recorded during the vortex encounters. |
| File Size | 2803537 |
| Page Count | 74 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980001023 |
| Archival Resource Key | ark:/13960/t7np70q6g |
| Language | English |
| Publisher Date | 1997-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Aircraft Models Vortices Wind Tunnel Tests Wakes Free Flight Wing Span Video Data Angle of Attack Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
