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Flight-measured laminar boundary-layer transition phenomena including stability theory analysis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Holmes, B. J. Obara, C. J. |
| Copyright Year | 1985 |
| Description | Flight experiments were conducted on a single-engine turboprop aircraft fitted with a 92-in-chord, 3-ft-span natural laminar flow glove at glove section lift coefficients from 0.15 to 1.10. The boundary-layer transition measurement methods used included sublimating chemicals and surface hot-film sensors. Transition occurred downstream of the minimum pressure point. Hot-film sensors provided a well-defined indication of laminar, laminar-separation, transitional, and turbulent boundary layers. Theoretical calculations of the boundary-layer parameters provided close agreement between the predicted laminar-separation point and the measured transition location. Tollmien-Schlichting (T-S) wave growth n-factors between 15 and 17 were calculated at the predicted point of laminar separation. These results suggest that for many practical airplane cruise conditions, laminar separation (as opposed to T-S instability) is the major cause of transition in predominantly two-dimensional flows. |
| File Size | 10534719 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850012808 |
| Archival Resource Key | ark:/13960/t5z65df2k |
| Language | English |
| Publisher Date | 1985-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Flight Tests Stability Laminar Flow Turbulent Boundary Layer Tollmien-schlichting Waves Boundary Layer Transition Airfoils Aerodynamic Coefficients Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
