Nonequilibrium flow over delta wings with detached shock waves
Copyright policy )Nonequilibrium flow over delta wings with detached shock waves
An analysis is made of the effect of streamwise density changes, due to chemical reactions, on the flow in the shock layer of a medium- to low-aspect-ratio delta wing at angles of incidence such that the shock wave is detached from the leading edges. It is shown that the flow retains the essentially conical character that is associated with the absence of density changes. Near the midspan of the wing, the density changes displace the shock wave toward the wing surface but do not alter the shock shape. The displacement effect predicted by the analysis is confirmed by experiments in a high-enthalpy shock tunnel.
- University of Queensland Australia
- University of Queensland Australia
- University of Queensland Australia
flow retains essentially conical character, Aerospace Engineering, chemical reactions, high-enthalpy shock tunnel, Existence, uniqueness, and regularity theory for compressible fluids and gas dynamics, Shock waves and blast waves in fluid mechanics, streamwise density changes, 2202 Aerospace Engineering, shock layer, medium- to low-aspect-ratio delta wing, Jets and cavities, cavitation, free-streamline theory, water-entry problems, airfoil and hydrofoil theory, sloshing, shock wave detached from leading edges
flow retains essentially conical character, Aerospace Engineering, chemical reactions, high-enthalpy shock tunnel, Existence, uniqueness, and regularity theory for compressible fluids and gas dynamics, Shock waves and blast waves in fluid mechanics, streamwise density changes, 2202 Aerospace Engineering, shock layer, medium- to low-aspect-ratio delta wing, Jets and cavities, cavitation, free-streamline theory, water-entry problems, airfoil and hydrofoil theory, sloshing, shock wave detached from leading edges
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