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

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 [Formula: see text], and the angle of attack, [Formula: see text], was varied in the range of [Formula: see text], mostly at [Formula: see text] and [Formula: see text] sideslip. In addition, the angle of sideslip, [Formula: see text], was varied at constant angles of attack up to [Formula: see text]. The Reynolds number, which was not explicitly changed, was in the range of [Formula: see text], 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.