Experimental investigation of unsteadiness in swept hypersonic shock-wave/boundary-layer interactions
Abstract
The proposed work will address fin-generated three-dimensional shock-wave/boundary-layer interactions (SWBLIs) under hypersonic inflow conditions, focusing on understanding and controlling unsteady aspects of these interactions. Fin-generated SWBLIs occur at the control surfaces of a variety ofhypersonic vehicles, including the ONR hypervelocity projectile. The unsteady pressure and heat-flux loads generated by such interactions at hypersonic conditions are poorly understood, and may affect vehicle survivability as well as the effectiveness of control surfaces. A comprehensive experimentalparametric study will first be performed on a flat-plate/fin geometry, varying the hypersonic Mach number, boundary-layer state, fin incidence angle and geometry, and wall temperature ratio. A range of time-resolved diagnostic techniques will be implemented to investigate SWBLI unsteadiness over thisparameter space: high-bandwidth surface pressure measurements, high-speed plan-view schlieren (both conventional and focusing), and fast-response temperature sensitive paint. Three-dimensional relieving effects from surface curvature will be examined by replacing the flat plate with a hollow cylinder section. Finally, attempts will be made to control the SWBLI unsteadiness in certain configurations through the introduction of micro-ramp vortex generators upstream of the interaction region; the influence of streamwise separation between the vortex generators and SWBLI will be investigated to determinewhether such a control strategy could be effective in flight geometries where the SWBLI position changes with actuation of the control surface.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jul 26, 2018
- Source ID
- N000141812518
Entities
People
- Stuart Laurence
Organizations
- Office of Naval Research
- United States Navy
- University of Maryland