Supersonic oblique shock-wave boundary layer interaction of free stream shock-wave perturbations with supersonic ground effect aerodynamics.

The response for this supersonic oblique shock-wave boundary layer interaction is to investigate the free-stream shock wave perturbations from supersonic ground effect.  The purpose for this project is to determine the lift-to-drag ratio from the free-stream shock wave perturbations from various ground clearances.

Supersonic ground effect aerodynamics provides a numerous review of work to help focus on applied research on wings and aircraft, present and future ground transportation, projectiles, and other related bodies. When developing methods for ground testing, most similar to a real system and most cost effective is the wind tunnel. The design for the configuration is horizontal opposed wedges with adjustable span wise distances that consist adjustable fin angles. The configuration consists of non-dimensional ground clearances of object as height ratio from: diameter, length and mean wing chord. These ratios will determine the most appropriate length scale for the given application. A Background Oriented Schlieren technique will be used to capture the images.

The results for this research for ground testing consists changes with the ground clearances leading perturbations that affect the induced drag and non-linearity of the ground-effect lifting flow of the system.