Open Access

ABSTRACT

Intersection of Slender Longitudinal Vortices by Shock Waves

E. Krause¹, W. Schröder¹, M. Klaas¹, O. Thomer¹

1 Aerodynamisches Institut, RWTH Aachen, D-52062 Aachen, Germany

The International Conference on Computational & Experimental Engineering and Sciences 2008, 5(1), 41-46. https://doi.org/10.3970/icces.2008.005.041

Abstract

In supersonic flow the leading edge vortex of delta wings can encounter intersection by an oblique or a normal shock. The resulting interaction between the two influences the aerodynamic forces, in particular the lift, especially if vortex breakdown occurs. This problem was studied in an idealized form by assuming an isolated slender vortex being intersected by an oblique and a normal shock, respectively. The investigation was carried out in two coordinated companion studies, one using numerical solutions of the Euler and Navier-Stokes equations, and the other experimental techniques, i. e. flow visualization methods, and Laser-Doppler and particle-image velocimetry. The measurements yielded profiles of the axial and azimuthal velocity components of the undisturbed vortex, distributions of the axial velocity component, visualizations of the shock deformation, and the deflection of the vortex core for the case of the oblique-shock-vortex interaction. The numerical solutions yielded detailed profiles of all flow quantities including those of vortex breakdown.

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