Experimental and Numerical Investigation of the Vortical Flow on the Transonic Missile LK6E2

Kurzfassung

This study analyzes the vortical flow around the generic transonic missile DLR-LK6E2 using wind tunnel data, complemented by numerical simulations. Pressure-sensitive paint and oil film interferometry proved highly effective, providing detailed insights into flow separations on the missile’s wings. Initially, two wings exhibited identical flow development; however, beyond a certain angle of attack—at a roll angle of and Mach 0.85—their flow behavior diverged. This asymmetry in flow development is reflected in the rolling moments as a distinct break in the angle-of-attack-dependent curve. Comparisons with RANS simulations revealed that the accurate numerical prediction of the rolling moments requires the capture of this flow asymmetry.