Abstract:

ESDU 75004 gives curves calculated from linearised theory for the wave drag of wings with straight leading- and trailing-edges, streamwise tips, and constant spanwise thickness/chord ratio. Data are given for taper ratios of 0, 0.5 and 1.0 for wings with symmetric parabolic arc or rhombic aerofoil section. Data are also given for taper ratios of 0 and 1.0 for a wing with a symmetric double-wedge aerofoil section with maximum thickness at 0.3 chord, and guidance is given on interpolating for other positions of maximum thickness. The data are plotted as a function of aspect ratio, thickness/chord ratio, Mach number and mid-chord sweep; flow/geometry conditions for sonic ridge lines and sonic trailing-edges are indicated. The data will find particular application in missile design.