Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow PDF Download
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Author: Maurice Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
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Book Description
An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Author: Maurice Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
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Book Description
An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1276
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Book Description
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1286
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 748
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Book Description
Author: Ephraim M. Sparrow
Publisher:
ISBN:
Category : Equations
Languages : en
Pages : 744
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Book Description
All the aforementioned results are given for fluids having Prandtl numbers in the range 0.01 to 1000.
Author: Herbert S. Ribner
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 738
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Book Description
The interaction of a convected field of turbulence with a shock wave has been analyzed to yield the modified turbulence, entropy spotiness, and noise generated downstream of the shock. This analysis generalizes the results of Technical Note 2864, which apply to a single spectrum component, to give the shock-interaction effects of a complete turbulence field. The previous report solved the basic gas-dynamic problem, and the present report has added the necessary spectrum analysis.
Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 516
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Book Description
Author: R. J. Volluz
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 512
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Book Description
Author: John D. Stanitz
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 734
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Book Description
A method of analysis is developed for two dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-blade impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.
Author: Robert W. Boucher
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 718
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Book Description
The angle of inclination of the principal axis was found to have probable error of plus or minus 0.17 degrees both from analysis of the error of inertia measurement of the full-scale airplane and from tests with a model having a simple configuration. Analysis showed the probable error of the inertia measurements for the test airplane to be plus or minus1.00, plus or minus 0.49, and plus or minus 0.35 percent of the true moment of inertia about the X, Y, and Z body reference axes, respectively.
