Effect of yaw at supersonic speeds on theoretical aerodynamic coefficients of thin pointed wings with several types of trailing edge

Expressions are obtained for the aerodynamic coefficients of pointed wings with three types of trailing edge.The derivais based on an equation previously derived for the pressure distribution on a thin yawed delta wi~at supersonic speeds.For a semivertex angle of tan-l 0.4, the effect of yaw on the lift coefficient, the wave-drag coefficient, the center of pressure, and the rolling-mmnent coefficient of a thin pointed wing is compared for three tyyes of trailing edge.Although the lift coefficient of a pointed wing may be increased by sweeping the trailing edges back from the center line, the variation of center of pressure and rolling moment with yaw angle is thereby tncreased.The variation of oenter of pressure and rolling moment with yaw angle is decreased when the trailing edges are swept back from the outer tips of the wing.The chordwise distance from the vertex of a symmetrical pointed wing to its center of pressure was found to be nearly independent of yaw angle for each of the types of trailing-edge sweepback investigated.