Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million

Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million
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Total Pages : 74
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ISBN-10 : UOM:39015095313881
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Rating : 4/5 (81 Downloads)

Synopsis Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million by : Anthony W. Fiore

Surface shear stress measurements were made in the Flight Dynamics Laboratory's M=3 High Reynolds Number wind tunnel. The primary purpose of this research was to make shear stress measurements at very high Reynolds numbers for near adiabatic wall and zero pressure gradient conditions. The results are presented as the local skin friction coefficient versus both the momentum thickness and the length Reynolds number. The investigation was conducted on the nozzle wall at a nominal Mach number of three over the Reynolds number range of 20,000

Technical Abstract Bulletin

Technical Abstract Bulletin
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Publisher :
Total Pages : 144
Release :
ISBN-10 : CORNELL:31924057184800
ISBN-13 :
Rating : 4/5 (00 Downloads)

Synopsis Technical Abstract Bulletin by :

NASA Technical Report

NASA Technical Report
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Total Pages : 50
Release :
ISBN-10 : MINN:30000011021841
ISBN-13 :
Rating : 4/5 (41 Downloads)

Synopsis NASA Technical Report by :

Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy

Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy
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Total Pages : 654
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ISBN-10 : STANFORD:36105024831781
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Rating : 4/5 (81 Downloads)

Synopsis Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy by : Alvin Seiff

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.

Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics
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Total Pages : 1078
Release :
ISBN-10 : RUTGERS:39030037542877
ISBN-13 :
Rating : 4/5 (77 Downloads)

Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics

R & D Abstracts

R & D Abstracts
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Total Pages : 534
Release :
ISBN-10 : STANFORD:36105014641588
ISBN-13 :
Rating : 4/5 (88 Downloads)

Synopsis R & D Abstracts by : Technology Reports Centre (Great Britain)