Development of transition criteria on the basis of e to the N power for three dimensional wing boundary layers
Abstract
Criteria for the laminar-turbulent transition on laminar flow airfoils were established for wing design purposes. Flight tests with the ATTAS research aircraft provided a data base for the experimental determination of N-factors where N = amplitude amplification exponent. Cross flow instability, Tollmein-Schlichting instability, and attachment line contamination were observed. The IR method provided a global picture of the transition line, without affecting the flow itself. Boundary layer stability analyses using the Orr-Sommerfeld solver SALLY for several flight conditions give N-factor threshold values for the Tollmein-Schlichting and for the cross flow instability. Curvature effects, compressibility effects, and interactions between the disturbances could not be taken into account.
- Publication:
-
Flows with Separation
- Pub Date:
- 1988
- Bibcode:
- 1988flws.rept..103B
- Keywords:
-
- Boundary Layer Transition;
- Structural Design Criteria;
- Three Dimensional Boundary Layer;
- Transition Flow;
- Aircraft Design;
- Boundary Layer Stability;
- In-Flight Monitoring;
- Laminar Boundary Layer;
- Laminar Flow Airfoils;
- Turbulent Boundary Layer;
- Wind Tunnel Tests;
- Fluid Mechanics and Heat Transfer