NACA-TN-2114

Abstract

The analysis is limited to wings of vanishingly small thickness that have zero camber. The results are valid only for a range of supersonic speeds in which the components of the free-stream velocity normal to the leading and trailing edges are supersonic. These conditions are now commonly expressed by the term "supersonic leading and trailing edges". The wing configurations considered in the analysis are defined by the information and sketches given in figures 1 and 2. All the data obtained in the analysis for the velocity potential and pressure distributions and for the derivatives c<em>l</em>_a and c<em>l</em>_p are applicable to the wings of the type shown in figure 1. These wings have sweptback leading edges, although the trailing edges may be either sweptback or swept-forward. A further restriction is that the Mach waves from either tip may not intersect the remote half-wing.