Wake Effect Studies on a Two-Dimensional Trailing Edge High Lift System.
Abstract
Experimental investigations were performed on a two component airfoil for studying the effects of the wake of the forward element on the development of the viscous flow on the upper surface of the flap. Measurements of the initial conditions, the boundary layer on the upper surface of the flap, and pressure distributions on the airfoil surfaces were obtained both in the presence and absence of the wake of the forward element. The nature of the viscous flow on the flap has been examined at angles of attack up to maximum lift coefficient conditions. Correlative analysis was performed to establish the validity and limits of applicability of the present boundary layer methods, confluent boundary layer method, and multi-component airfoil program for the prediction of the aerodynamic performance characteristics. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 22, 1974
- Accession Number
- AD0787141