Aerodynamic Performance of Delta Wings at Supersonic Speeds

Abstract

In recently published papers the authors have discussed the problem of drag of delta wings with straight trailing edges and also the lift of this type of wing. The present paper consists of an extension of these results to delta wings with swept-back or swept-forward trailing edges. Drag at zero lift for two slope surfaces and lift is computed for these airfoils, and a discussion is given of the drag due to lift. Centers of pressure are also computed. In addition, some results for drag of wings with three slope surfaces are given. Discussion is made of optimum design from the standpoint of leading and trailing edge angles, and location of maximum thickness. I t is shown that considerable improvements over two-dimensional airfoil performance can be obtained. Results are presented in the form of conventional engineering coefficients.