Effect of aspect ratio and taper on the pressure drag at supersonic speeds of unswept wings at zero lift

The linear theory for determining the pressure distribution at supersonic speeds on wings of syzmmtrical section at zero lift has been used to calculate the pressure drag coefficients at zero lift of the family of unswept, untwisted wings with the diamond profile.On the basis of the method of R. T.Jones, which was presented In NACA TN No. 1107, a general expression has been foumi for the drag ccefflclent at any supersonic Mach num"er, aspect ratio, and taper.The general expression, which 1s too unwieldy for use in analysis, has been used in the construction of nondimensional charts permitting a rapid estimation of the drag coefficient for a given whg at any.Mch number.For wings of diamond or rectangular plan form the general e~ression reduces to simple formulas for the drag coefficients.The nondimensional charts indicate t~t, at very low aspect ratios, wings of diamond plan form have the least drag and that increasing the ratio of tip ohord to root chord increases the drag -kedly.However, at krge aspect ratios rectangular wings have the least drag and decreasing the ratio of tip chord to root chord increases the drag slightly.