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Supersonic boundary-layer transition on the larc f-106 and the dfrf f-15 aircraft. part 1: transition measurements and stability analysis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rose, Ollie J. Miller, D. S. Johnson, Joseph B. Collier Jr., Fayette S. |
| Copyright Year | 1987 |
| Description | For the case of the F-15 flight tests, boundary layer transition was observed up to Mach numbers of 1.2. For very limited and specific flight conditions, laminar flow existed back to about 20 percent chord on the surface clean up glove. Hot film instrumentation was effective for locating the region of transition. For the F-106 flight tests, transition on the wing or vertical tail generally occurred very near the attachment line. Transition was believed to be caused by either attachment line contamination or strong cross flow development due to the high sweep angles of the test articles. The compressibility analysis showed that cross flow N-factors were in the range of 5 to 12 at transition. |
| File Size | 9517212 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19900003242 |
| Archival Resource Key | ark:/13960/t6838pw1d |
| Language | English |
| Publisher Date | 1987-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Flight Tests Supersonic Aircraft Laminar Flow Sweep Effect Pressure Distribution Fuel Consumption Boundary Layer Transition Boundary Layer Stability Supersonic Boundary Layers Boundary Layer Control Cross Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
