Computational investigation of the flow structure over a pitching delta wing at supersonic speeds

Abstract

Compressible flows over a 60° sweep delta wing with a sharp leading edge undergoing pitching oscillations are computationally studied. Emphasis in this study is on possible supersonic flow structures and their variations during the pitching motion of a delta wing. Unstructured grid, k-ωSST turbulence model and a dual-time implicit time integration are used. Accurate simulations are performed for various Mach number and angles of attack to cover different flow structures and phenomena associated with them. Variations of flow patterns in a crossflow plane, pressure coefficient on the wing surface, and hysteresis loops associated with vortex core location during a pitching cycle are investigated. The trends with Mach number, mean angle of attack, amplitude of pitching and pitching frequency are illustrated.

Computational Investigation of Vortex Breakdown over a Pitching Delta Wing at Supersonic Speeds

“…Di erent versions of k ! turbulent model have been found to be appropriate for capturing vortex ow over delta wings by several researchers [21][22][23][24]. Schiavetta et al [22] compared the Detached Eddy Simulation (DES) and Unsteady Reynolds-Averaged Navier-Stokes (URANS) turbulence modeling methods for prediction of unsteady vortical ows over delta wings.…”

“…Instead, the breakdown behaviors associated with them are discussed in the next section. The authors [24] have simulated the various cross ow patterns over the stationary and pitching delta wing and have veri ed their results with experimental data. Figure 5 shows local Mach number contour map and total pressure contour lines in the cross ow plane at 30% chordwise station for the ow with free-stream Mach number of 0.8 and angle of attack of 20 .…”