A Note on the Wave Drag of “Exposed” Rectangular Wings

Abstract

This Note Gives a simple relationship between the zero-lift wave drag of the wing of a rectangular wing and body combination and the wave drag of the portion of the gross wing blanketed by the body, both evaluated as if isolated (i.e.ignoring the interference of other parts of the combination). The result is valid only when the tip Mach cones of the wing lie downstream of the blanketed wing. Detailed results are given for the case of wings with double-wedge section, the maximum thickness being at mid-chord.

An extension of the linearized theory of supersonic flow past quasi-cylindrical bodies, with applications to wing-body interference

“…is the two-dimensional wave drag coefficient for the given wing section ; and if the aspect ratio A = 2(s -Ro) of the exposed wing is restricted, as in $5.3, to be greater than 2/P, then equation (109 (110) The first term represents the drag of the exposed wing panels joined together, so that the interference drag ratio kD, is obtained as where CDl is the drag coefficient of the portion of the wing blanketed by the body, whose aspect ratio is 2/(/3c) in the notation of $ 5 . (This result has also been obtained by Sheppard (1957).) Equation (111) suggests that k,, = 1 for 0 < c < 2, and that k , , < 1 for c > 2.…”