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Transition flight experiments on a swept wing with suction (Document No: 20040161129)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Maddalon, D. V. Montoya, L. C. Collier Jr., F. S. Putnam, R. J. |
| Copyright Year | 1989 |
| Description | Flight boundary-layer transition experiments were conducted on a 30 degree swept wing with a perforated leading-edge suction panel. The transition location on the panel was changed by systematically varying the location and amount of suction. Transition from laminar to turbulent flow was due to leading-edge turbulence contamination or crossflow disturbance growth and/or Tollmien-Schlichting disturbance growth, depending on flight condition and suction variation. Amplification factor correlations with transition location were made for various suction configurations using a state-of-the-art linear stability theory which accounts for body and streamline curvature and compressibility. |
| File Size | 676615 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040161129 |
| Archival Resource Key | ark:/13960/t15n1428z |
| Language | English |
| Publisher Date | 1989-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Suction Turbulent Flow Flight Conditions Compressibility Swept Wings Laminar Flow Boundary Layer Transition Leading Edges Cross Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
