A Quiet Tunnel Investigation Of Hypersonic Boundary Layer Stability Over A Cooled Flared Cone

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A Quiet Tunnel Investigation of Hypersonic Boundary-Layer Stability Over a Cooled, Flared Cone
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Authors: National Aeronautics and Space Administration NASA
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A flared-cone model under adiabatic and cooled-wall conditions was placed in a calibrated, low-disturbance Mach 6 flow and the stability of the boundary layer w
An Experimental Investigation of Wall-Cooling Effects on Hypersonic Boundary-Layer Stability in a Quiet Wind Tunnel
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One of the primary reasons for developing quiet tunnels is for the investigation of high-speed boundary-layer stability and transition phenomena without the tra
Hypersonic Boundary Layer Stability Over a Flared Cone in a Quiet Tunnel
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Hypersonic Boundary-Layer Stability Experiments on a Flared-Cone Model at Angle of Attack in a Quiet Wind Tunnel
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An experimental investigation of the effects of angle of attack on hypersonic boundary-layer stability on a flared-cone model was conducted in the low-disturban
Hypersonic Boundary Layer Stability Experiments in a Quiet Wind Tunnel with Bluntness Effects
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Type: BOOK - Published: 2018-07-25 - Publisher: Createspace Independent Publishing Platform

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Hypersonic boundary layer measurements over a flared cone were conducted in a Mach 6 quiet wind tunnel at a freestream unit Reynolds number of 2.82 million/ft.