Experimental Study of Nozzle Wall Boundary Layers at Mach Numbers 20 to 47 PDF Download
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Author: Joseph H. Kemp
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 116
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Book Description
The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
Author: Joseph H. Kemp
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 116
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Book Description
The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
Author: Joseph H. Kemp
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 7
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 460
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Book Description
Author: Edgard Backx
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 64
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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 590
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Book Description
Author: William D. Harvey
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Book Description
Author: Bill Harvey
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 40
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 802
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Author: Jan Lepicovsky
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 0
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Book Description
An experimental investigation of the effects of nozzle operating conditions on the development of nozzle-exit boundary layers of highly heated air free jets is reported in this paper. The total pressure measurements in the nozzle-exit boundary layer were obtained at a range of jet Mach numbers from 0.1 to 0.97 and jet total temperatures up to 900 K. The analysis of results shows that the nozzle-exit laminar boundary-layer development depends only on the nozzle-exit Reynolds number. For the nozzle-exit turbulent boundary layer, however, it appears that the effects of the jet total temperature on the boundary-layer integral characteristics are independent from the effect of the nozzle-exit Reynolds number. This surprising finding has not yet been reported. Further, laminar boundary-layer profiles were compared with the Pohlhausen solution for a flat-wall converging channel and an acceptable agreement was found only for low Reynolds numbers. For turbulent boundary layers, the dependence of the shape factor on relative Mach numbers at a distance of one momentum thickness from the nozzle wall resembles Spence's prediction. Finally, the calculated total pressure loss coefficient was found to depend on the nozzle-exit Reynolds number for the laminar nozzle-exit boundary layer, while for the turbulent exit boundary layer this coefficient appears to be constant.
