Effects of slight nose bluntness and roughness on boundarylayer transition in supersonic flows volume 12 issue 4 j. A new transitionturbulence model considering the modes of instability and the compressibility effects is established. Stability and transition of hypersonic boundarylayer flows dtic. Transitional shockwaveboundarylayer interactions in hypersonic. Boundarylayer transition on a cone and flat plate at mach. Boundary layer transition poses a problem for hypersonic vehicles as surface heat flux and temperatures are dramatically increased at the transition point, possibly resulting in structural failure. Hypersonic boundarylayer transition for x33 phase ii. Aspects of hypersonic boundary layer transition control. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. Effects of slight nose bluntness and roughness on boundary.
Hypersonic boundary layer transition and control 7 fig. Transition and turbulence production in a hypersonic boundary layer is investigated in the mach 6 wind tunnel at peking university, using rayleigh scattering. Transition and turbulence production in a hypersonic boundary layer is investigated in a mach 6 wind tunnel using rayleighscattering visualization, fastresponse pressure measurements, and particl. Boundary layer transition and surface roughness effects in. Modeling flow transition in hypersonic boundary layer. Transitional shockwaveboundarylayer interactions in. Boundarylayer flow near the trailing edge of a flat plate. This boundary layer transition ii wedge will be launched on a sounding rocket sometime in 2021 from nasas wallops flight facility in virginia. Experimental evidence indicates that boundary layers in hypersonic flows transition from being laminar to turbulent via the mechanism of formation and propagation of turbulent spots. Hypersonic boundary layer transition measurements using. Pdf hypersonic boundary layer transition and control. Goldstein 1 has given a solution to the boundarylayer equations for the flow just downstream from the trailing edge of a flat plate. Transition modeling for low to high speed boundary layer flows with cfd. Numerical study of hypersonic reacting boundary layer transition on cones physics of fluids, vol.
Hypersonic boundarylayer transition for x33 phase ii vehicle. Modeling of supersonichypersonic boundary layer transition. Transition and turbulence production in a hypersonic boundary layer is investigated in the mach 6 wind tunnel at peking university, using rayleighscattering. Flatplate boundarylayer transition in hypersonic flows stanford. Transitional shock waveboundary layer interactions in hypersonic flow article in journal of fluid mechanics vol. It is shown here that this approximation is no longer valid i. Transition modeling for low to high speed boundary layer flows. Hypersonic boundary layer transition visualization in. Designed for advanced undergraduate and graduate engineering courses in modern boundarylayer theory, this volume also serves as a valuable reference for professionals. The simulation of laminarturbulent tran sition in boundarylayer flows for entry scenarios can deliver estimates of flightrelevant physical properties such as drag. Laminarturbulent transition and shock waveboundary layer interaction. Laminarturbulent transition problems in supersonic and hypersonic flows. Following the trend for reducing the number of transition equations, a novel. Besides, asymmetric transition leads to drag asymmetry and a pressure imbalance causes side forces, which impacts vehicle dynamics and controllability.
Transition of hypersonic flow past flat plate with. A new parameter that appears to correlate for boundarylayer flow was found. Prediction and control of laminarturbulent transition in high. Boundary layer transition and surface roughness effects in hypersonic flow. Transition correlation in threedimensional supersonic boundary layers, h. In addition, the book presents useful equations for calculating heat transfer between reacting gas boundary layers and reacting, melting, sublimating, and otherwise decomposing surfaces. The nonlinear interactions of the instability modes in a hypersonic laminar boundary layer undergoing natural transition are examined using bispectral analysis. Transitional shockwaveboundarylayer interactions in hypersonic flow volume 752. Boundarylayer transition is a problem that has plagued several generations of. To achieve higher reynolds numbers in the 31inch mach 10 facility, either the facility stagnation pressure, model angleofattack aoa, or both must be increased. Pdf during the process of aerodynamic shape design of supersonic and hypersonic space planes, laminar flow design and boundary layer.
1135 995 526 867 606 285 201 519 1343 311 106 1393 1518 1473 722 1320 1048 1269 979 310 726 234 103 1395 1541 1097 692 681 961 1200 755 779 639 903 1057 1033 1175 634