Boundary Layer Study on Nozzle Wall at Hypersonic Velocities PDF Download
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Author: Kenneth Morris Jones
Publisher:
ISBN:
Category :
Languages : en
Pages : 276
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Book Description
Author: Kenneth Morris Jones
Publisher:
ISBN:
Category :
Languages : en
Pages : 276
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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: 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: A. J. Smits
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 22
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Book Description
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: 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: Ross G. Luce
Publisher:
ISBN:
Category :
Languages : en
Pages : 57
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Book Description
An experimental and analytic investigation of the influence of wall cooling on conical hypersonic nozzles operated at moderately low Reynolds numbers is reported. The experimental program consisted of nozzle static pressure distributions and impact pressure surveys of a nominal M = 12, 3-inch exit diameter conical nozzle equipped with a coolant tank to allow for the adjustment of the wall temperature. Various coolants (water, freon-dry ice mixture, and liquid nitrogen) were used to provide selected wall temperatures down to 210R. The measurements showed a 25% reduction of the displacement and boundary layer thicknesses when referred to a nozzle equilibrium temperature of 670R. The momentum integral technique was used to formulate a digital computer program to examine the wall cooling effects on hypersonic axisymmetric nozzles. A Pr number of one is assumed. Fourth order velocity and total enthalpy profiles were used. These profiles were adjusted to account for wall temperature, transverse curvature, and pressure gradient. Results from this computer program were confirmed by the experiments. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 652
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Book Description
Author: Norman Ellis Scaggs
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 78
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Book Description
An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
Author: John C. Adams
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
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Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
