Numerical Study of the Turbulent Boundary Layer in a Hypersonic Nozzle PDF Download
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Author: Joan Patricia Gosink
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 148
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Author: Joan Patricia Gosink
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 148
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Book Description
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.
Author: William D. Harvey
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 92
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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: Paul Joseph Shall (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
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Book Description
An experimental investigation was made to determine the structure and integrated properties of turbulent boundary layers in hypersonic nozzles, at Mach numbers between 10 and 12. It is concluded that the 1/7-power velocity profile does not agree with the experimental data in this Mach number range. However, a velocity profile based on the Crocco energy relations agrees well with the data as does the corresponding temperature profile, except at the point of maximum temperature. The semi-empirical relationships for boundary layer thickness and displacement thickness, proposed by Burke are strongly supported by the experimental data of this study. (Author).
Author: Arnold Polak
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 56
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Book Description
Results of a study of hypersonic-turbulent boundary-layer separation over axisymmetric bodies are presented. Pressure, heat-transfer and flow visualization data were obtained for a cone-cylinder-flare configuration. The experimental data were correlated with a theoretical prediction. (Author).
Author: E. T. Fick
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: John B. Anders
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
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Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
Author: J. P. Kreskovsky
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 102
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Book Description
Author: Edgard Backx
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 64
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Book Description
