Supersonic Wave Drag of Nonlifting Sweptback Tapered Wings with Mach Lines Behind the Line of Maximum Thickness

Wave drag equations are derived for rhombic-profile tapered wings with maximum-thickness line swept less than the Mach line. Variations in drag with taper ratio, aspect ratio, sweepback, and Mach number are determined. Calculations are presented for representative plan forms and for a family of wings having equal root bending stress.