Experimental and numerical investigations were performed on a laminar hypersonic compression corner flow. The formation of streamwise vortices is a phenomenon inherent to the shock-wave boundary-layer interaction of such flows. To assess the influence of different separation bubble geometries on the formation of those vortices, a natural suction was applied on the hinge-line of a ramp model. The suction allowed an isolated manipulation of the separation bubble with an otherwise unchanged flow over the ramp. The experiments were conducted in the Hypersonic Aachen Shock Tunnel TH2 at a Mach number of 7.9. Corresponding direct numerical simulations (DNS) were carried out using the in-house DNS-solver KICK. The experiments demonstrate that the curvature of the separated shear layer at reattachment as measured from schlieren images does not describe the occurring flow instability. The numerical investigations show that vortex tilting initializes vorticity in streamwise direction upstream of the hinge-line in either case with and without suction. Further downstream of the hinge-line, vortex stretching becomes the dominant vorticity transport term. In all investigated cases, kinematic vorticity transport terms were dominant over baroclinic effects.