Predictions for the Heat Transfer and Boundary Layer Growth in the Radiatively Driven Hypersonic Wind Tunnel and Camparisons with Experiment at Ultra High Reynolds Number (invited) PDF Download
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Author: G. L. Brown
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Category :
Languages : en
Pages :
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Author: G. L. Brown
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 596
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 724
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Author: Alvin Seiff
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 654
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Book Description
Heat-transfer data from four wind-tunnel experiments and two free-flight experiments with turbulent boundary layers have been examined to see whether or not they are well represented by the Reynolds analogy or a modification thereof. The heat-transfer results are put into the form of dimensionless Stanton numbers based on fluid properties at the outer edge of the boundary layer and are compared with skin-friction coefficients for the same Mach numbers and wall to free-stream temperature ratios as obtained from an interpolation of the existing skin-friction data. The effective Reynolds number is taken to be the length Reynolds number measured from the effective turbulent origin, a position which differs importantly from the leading edge of the test surface in some cases.
Author: Mitchel H. Bertram
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Category :
Languages : en
Pages : 40
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Author: Alan E. Blanchard
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Category : Aerodynamics, Hypersonic
Languages : en
Pages : 120
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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 transition-promoting effects of acoustic radiation from tunnel walls. In this experiment, a flared-cone model under adiabatic- and cooled-wall conditions was placed in a calibrated, "quiet" Mach 6 flow and the stability of the boundary layer was investigated using a prototype constant-voltage anemometer. The results of this experiment were compared with linear-stability theory predictions and good agreement was found in the prediction of second-mode frequencies and growth. In addition, the same "N = 10" criterion used to predict boundary-layer transition in subsonic, transonic, and supersonic flows was found to be applicable for the hypersonic flow regime as well. Under cooled-wall conditions, a unique set of continuous spectra data was acquired that documents the linear, nonlinear, and breakdown regions associated with the transition of hypersonic flow under low-noise conditions
Author: Kenneth F. Stetson
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ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 92
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Author: Davis H. Crawford
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Category : Aeronautics
Languages : en
Pages : 680
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At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Author:
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Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
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Author: Dennis M. Bushnell
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 44
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Book Description
Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
