The Laminar Boundary Layer in Axisymmetric Hypersonic Nozzles with Wall Cooling PDF Download
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Author: Ross G. Luce
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 0
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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: Ross G. Luce
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 0
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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: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722791766
Category :
Languages : en
Pages : 60
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Book Description
The objective of the research is to understand supersonic laminar flow stability, transition, and active control. Some prediction techniques will be developed or modified to analyze laminar flow stability. The effects of supersonic laminar flow with distributed heating and cooling on active control will be studied. The primary tasks of the research applying to the NASA/Ames Proof of Concept (POC) Supersonic Wind Tunnel and Laminar Flow Supersonic Wind Tunnel (LFSWT) nozzle design with laminar flow control are as follows: (1) predictions of supersonic laminar boundary layer stability and transition, (2) effects of wall heating and cooling for supersonic laminar flow control, and (3) performance evaluation of POC and LFSWT nozzles design with wall heating and cooling effects applying at different locations and various length. Lo, Ching F. Unspecified Center...
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:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 780
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Book Description
Author: J. A. Durand
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 1
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Book Description
A new method for the estimation of boundarylayer thickness corrections to the contours of cooled axisymmetric nozzles for low-density, hypersonic flows is presented. Laminar flows of real gases in thermodynamic equilibrium with possible variation of specific heats, frozen flows, and boundary-layer thicknesses of the order of nozzle radii are considered. The derivation combines an appropriate integral momentum relation with an approximate friction law based on local similarity. Results of application of the method to several typical cases are shown to agree closely with experimental data. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
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Book Description
Author: David L. Whitfield
Publisher:
ISBN:
Category :
Languages : en
Pages : 92
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Book Description
The viscous flow region in low density hypersonic axisymmetric nozzles was investigated both theoretically and experimentally. Nonsimilar solutions were obtained for the internal laminar boundary layer equations which include second-order transverse curvature terms. These solutions were obtained on a CDC 1604 digital computer. Four existing low density axisymmetric nozzles were considered. Numerical solutions were obtained for these nozzles using various plenum chamber conditions and wall temperature distributions. The plenum chamber conditions used in the numerical solutions for these nozzles produced a test section Mach number range of about 3.0 to 18.0 and a test section Reynolds number per foot range of about 1000 to 15,000. Some results of the numerical solutions are compared with experimental measurements of pitot pressure, relative heat flux, and nozzle wall heat transfer coefficients. In all comparisons the numerical solutions appear to be consistent with the experimental data. (Author).
Author: Max Kinslow
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 40
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Book Description
The potential value of controlled boundary-layer removal from the wall of a nozzle for low-density hypersonic flow was investigated in a brief experimental program. A particular objective was the achievement of sufficient control over boundary-layer thickness to enable a contoured nozzle to be operated under off-design conditions without excessive deterioration of flow uniformity. The nozzle contour was greatly influenced by boundary-layer thickness. Boundary-layer removal involved suction through perforated walls where local nozzle static pressures exceeded the pressure in the large tank which enclosed the nozzle and test section.
Author: Arlo F. Johnson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 26
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Book Description
The excellent agreement between measured boundary layer thickness and thickness calculated by Sivells and Payne recommends their method for calculating turbulent boundary layer growth in axisymmetric hypersonic nozzles. It was thought worthwhile to adapt their approach to the laminar boundary layer. This analysis, along with a limited amount of corroborating data, is presented herein.
Author: Kenneth F. Stetson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 116
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Book Description
This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
