Measurements of an axisymmetric hypersonic shear-layer instability on a cone-cylinder-flare in quiet flow
Elizabeth K. Benitez, Matthew P. Borg, Pedro Paredes, Steven P. Schneider, Joseph S. Jewell
Abstract
Compression corners are commonly present along aircraft, such as at control surfaces, and can cause shock/boundary-layer interactions when the vehicle moves at supersonic or hypersonic speeds. By generating a separation bubble at the corner, a shear layer is present in the flow, which can potentially amplify instabilities, leading to a boundary-layer transition downstream of reattachment. We show, through experiments conducted under low-disturbance Mach-6 flow, the amplification of such a shear-layer instability by comparing measurements from two cone-cylinder-flare geometries with computations of the same.
Topics & Concepts
Hypersonic speedMechanicsBoundary layerMach numberSupersonic speedPhysicsInstabilityChoked flowShock (circulatory)Aerospace engineeringEngineeringMedicineInternal medicineFluid Dynamics and Turbulent FlowsComputational Fluid Dynamics and AerodynamicsPlasma and Flow Control in Aerodynamics