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Experimental Investigation of Unsteady Shock Wave Turbulent Boundary Layer Interactions About a Blunt Fin60,99 €![Characterization of the Global Hawk Low Pressure Turbine First Rotor]( "Characterization of the Global Hawk Low Pressure Turbine First Rotor")
Characterization of the Global Hawk Low Pressure Turbine First Rotor60,99 €![Experimental and Theoretical Studies in Low Temperature Physics: Sublimation and Vapor Pressure of Ar 36 and the Combined Effects of Phonon Attenuatio]( "Experimental and Theoretical Studies in Low Temperature Physics: Sublimation and Vapor Pressure of Ar 36 and the Combined Effects of Phonon Attenuatio")
Experimental and Theoretical Studies in Low Temperature Physics: Sublimation and Vapor Pressure of Ar 36 and the Combined Effects of Phonon Attenuatio60,99 €![Study Of Varying Boundary Layer Height on Turret Flow Structures]( "Study Of Varying Boundary Layer Height on Turret Flow Structures")
Study Of Varying Boundary Layer Height on Turret Flow Structures60,99 €![Non-Linear Boundary-Layer Receptivity Due to Distributed Surface Roughness]( "Non-Linear Boundary-Layer Receptivity Due to Distributed Surface Roughness")
Non-Linear Boundary-Layer Receptivity Due to Distributed Surface Roughness60,99 €![The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics]( "The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics")
The Combined Effects of Freestream Turbulence, Pressure Gradients, and Surface Roughness on Turbine Aerodynamics60,99 €![Boundary Layer Control of a Circular Cylinder Using a Synthetic Jet]( "Boundary Layer Control of a Circular Cylinder Using a Synthetic Jet")
Boundary Layer Control of a Circular Cylinder Using a Synthetic Jet60,99 €
A detailed investigation of the flow physics occurring on the suction side of a simulated Low Pressure Turbine (LPT) blade was performed. A contoured upper wall was designed to simulate the pressure distribution of an actual LPT blade onto a flat plate. The experiments were carried out at Reynolds numbers of 100,000 and 250,000 with three levels of freestream turbulence. Freestream turbulence levels ranging from 0.8% to 3% was used in this experiment. Smoke-wire flow visualization data was used to confirm that the boundary layer was separated and formed a bubble. Hot-wires (single and x-wire) and surface mounted hot-film gases and static pressure taps were used to map the flowfield. The transition process over the separated flow region is observed to be similar to a laminar free shear layer flow with the formation of a large coherent eddy structure. For each condition, the locations defining the separation bubble were determined by careful examination of pressure and mean velocity profile data. Transition onset location and length determined from intermittency profiles decrease as freestream turbulence levels increase. Additionally, the length and height of the laminar separation bubbles were observed to be inversely proportional to the levels of freestream turbulence.