Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Abstract

An investigation was conducted in the Langley 8-foot transonic tunnels to determine the aerodynamic loading characteristics of a thin conical cambered low-aspect-ratio delta wing in combination with a basic body and a body indented symmetrically for a Mach number of 1.2 in accordance with the supersonic area rule. The tests were conducted at Mach numbers from 0.60 to 1.12 and at 1.43 and at angles of attack generally from -4° to 20°. The wing vas conically cambered over the outboard 15 percent of each semispan. The wing had an aspect ratio of 2.31, 60° sweepback of the leading edge, and had NACA 65A003 airfoil sections parallel to the model plane of symmetry over the uncambered portion.

The results of this investigation indicate that a leading-edge separation vortex forms at moderate angles of attack and causes the shape of the span load distribution to change markedly. Significant center of pressure movements are noted at transonic speeds. Indenting the body in accordance with the supersonic area rule had little effect on the aerodynamic loading characteristics. Comparisons with expert mental data for a similar plane wing indicates that the cambered wing is considerably more effective than the plane wing in utilizing the leading edge suction forces to produce thrust. A comparison between experimental and theoretical results indicates fair agreement around sonic speeds.