Shock wave-boundary layer interactions take place in many vehicle configurations of practical importance such as wing–body junctures, deflected control surfaces, high-speed inlets and forward-facing steps. The associated flowfield becomes complex when the interaction causes flow to separate. A parametric study is carried out for supersonic flow past a compression–decompression ramp (CDR), to determine the ramp inclination angle that minimizes the adverse effect of separated flow. The inclination angle below which weak interaction occurs is obtained from the numerical simulations.
Parametric Study of Turbulent Flow Past a Compression–Decompression Ramp
Lect.Notes Mechanical Engineering
Design and Development of Aerospace Vehicles and Propulsion Systems ; Chapter : 2 ; 15-24
2021-03-19
10 pages
Article/Chapter (Book)
Electronic Resource
English