Experimental Investigation of Three-Dimensional Vortex-Airfoil Interaction in A Supersonic Stream
Abstract
An experimental study involving interaction between streamwise wing- tip vortices and a two-dimensional lifting surface in a supersonic stream was conducted. The experiments were designed to simulate interaction of supersonic vortices with aerodynamic surfaces of high-speed aircraft and missiles. The experimental scheme involves positioning an instrumented two-dimensional wedge downstream of a semi-span wing so that the trailing tip-vortex from the wing interacts with the aerodynamic surface. Experimental results indicate that the interaction strongly depends on the vortex strength and vortex proximity to the wedge leading edge. In their most organized form, distortion of streamwise vortices upon interacting with the wedge was found to result in formation of symmetric detached shock fronts far upstream of the wedge leading edge followed by an apparent slip surface separating a subsonic region from a supersonic zone. Interaction of vortices with oblique shock wave over the wedge section indicates that interaction of a relatively weak vortex with a moderate strength oblique shock does not lead to significant changes in the vortex structure. On the other hand, interaction of a moderate strength vortex with a strong oblique shock results in the formation of a detached shock wave upstream of the oblique shock front.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1993
- Accession Number
- ADA275107
Entities
People
- Iraj M. Kalkhoran