Development of Theoretical Method for Two-Dimensional Multi-Element Airfoil Analysis and Design. Part II: Leading-Edge Slat Design Method.
Final rept. 24 May 71-12 Jun 72,
GENERAL DYNAMICS FORT WORTH TEX CONVAIR AEROSPACE DIV
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A method has been developed for the design of leading-edge slats that produce a specified pressure distribution on the main airfoil. The method of distributed singularities is applied in a unique manner. The airfoil is represented in the conventional manner by a vortex sheet having the same shape as the airfoil. The slat is represented by a vortex sheet and a source line. The source line provides the slat thickness the vortex sheet provides the camber. A closed slat shape is guaranteed by requiring that the net mass added to the system be zero and that the stream function at the slat leading-edge stagnation point have the same value as at the trailing edge. It was found that valid solutions are possible only when the source line at least approximates a streamline generated by the airfoil without the slat. The slat shape is computed by locating the body streamline of the slat. A constrained least-square analysis provides this definition. Several sample designs are discussed. Detailed instructions for application of the method are provided. Details regarding the associated computer program are included. Author