Multiswept Wing Planform Study at Subsonic, Transonic, and Supersonic Speeds

Abstract

The effect of different wing planforms on the forces and moments as well as on the vortex flow over a multiswept tailless delta-wing configuration is investigated. The objective is to identify geometry parameters that result in favorable stability characteristics, the latter being significantly influenced by the vortex flow. To this end, the generic DLR-F22 multiswept delta-wing model was tested in its baseline version and with four additional multiswept wing planforms differing in leading-edge vortex controller (LEVCON) span and strake length. The integral forces and moments as well as the pressures on the lee side of the model were determined in separate entries in the transonic wind tunnel DNW-TWG. The Mach numbers considered were between M = 0.50 and 2.00, and the angle of attack, α, was varied in the range of 0° ≤ α ≤ 30°, mostly at 0° and 5° sideslip. In addition, the angle of sideslip, β, was varied at constant angles of attack up to β = +/- 10°. The Reynolds number, which was not explicitly changed, was in the range of 1.75–2.45 ⋅ 10^6, depending on the Mach number. It is found that the aerodynamic stability characteristics of the multiswept configuration generally improve as both LEVCON span and strake length increase.