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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 \(45^\circ \) 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.

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

  • 会议论文

  • 发表日期：

    2026年

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  • Christian Schnepf,
  • Erich Schülein

摘要

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 \(45^\circ \) 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.