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  • 1
    Electronic Resource
    Electronic Resource
    Hypersonic flow over a six-finned configuration (1988)
    Springer
    Experiments in fluids 6 (1988), S. 237-242 
    Details
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract Experimental data of the flow field over a six-finned configuration are compared with computations from an inviscid Euler code and a parabolized Navier-Stokes (PNS) code to assess their accuracy. Surface oil flow patterns, surface pressures, and flow field pilot surveys are presented. The PNS computations are in good agreement with the measurements in the inviscid regions. Differences are noted in the viscous regions possibly due to nose tip bluntness effects and the associated entropy layer.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00187363
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Hypersonic flow over a six-finned configuration (1988)
    Springer
    Details
    Publication Date: 1988-01-01
    Print ISSN: 0723-4864
    Electronic ISSN: 1432-1114
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 3
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    An experimental and analytical investigation of the aerodynamics of a hypersonic vehicle at free stream Mach 6 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The goal of this research is the assessment of the validity of existing three dimensional numerical programs in the prediction of the flow fields about general three dimensional hypersonic bodies. A detailed experimental research program was performed in which surface and flow field pressures were mapped. The results of the experimental work were compared with existing inviscid programs. Improvements were made on the existing numerical methods to include angle of attack. A summary of this work is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-164133
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Prediction and evaluation of eddy-viscosity models for free mixing (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis for the turbulent mixing of free jets is presented in this paper and compared to recent experimental results. A turbulent mass diffusion model is presented and is based on the concentration potential core. The model yielded good results when compared with the experimental results except for low-speed flows where few experimental data are available. A review of recent experimental results verifies again that the three diffusion processes in turbulent mixing are interrelated; however, no single diffusion model may be used for all three processes. This is especially true when pressure gradients are present in the flow field. It is shown that even though momentum diffusion is significantly affected by pressure gradients, mass diffusion is not. It is further indicated that the mass diffusion model has been derived and is based on the accurate correlations of experimental results obtained for the concentration potential core. Similar techniques may be used in deriving an expression for the momentum and thermal diffusion coefficients. These expressions would be more complicated since they would have to take care of the boundary layer at the start of the mixing region. Finally, a comparison of the analyses, using this particular model and Ferri's model, with available experimental results is made.
    Keywords: FLUID MECHANICS
    Type: NASA. Langley Res. Center Free Turbulent Shear Flows, Vol. 1; p 327-360
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An experimental investigation of vortex generation in a turbulent boundary layer undergoing adverse pressure gradient (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The existence of streamwise vortices in nominally 2-dimensional boundary layers undergoing adverse pressure gradient was investigated. The free stream Mach number was 5.75, the wall to stagnation temperature ratio was 0.63 and the Reynolds number based on free stream conditions was 3.9 x 10 to the 7th power/ft. The model consisted of an axisymmetric compression flare preceded by a cylindrical axially symmetric body. A natural turbulent boundary layer was established well ahead of the compression region. Boundary layer profiles of static pressure, pitot pressure, and stagnation temperature were taken at a surface station with a local inclination of 20 deg. Profile measurements were obtained at various peripheral stations. The measurements revealed zero peripheral variations at the surface of the body and at the edge of the boundary layer. However, distinct wavy pressure variations were observed within the boundary layer profiles, indicating the existence of longitudinal vortex cells within the boundary layer.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-2037
    Format: application/pdf
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  • 6
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    Skin friction reduction by slot injection at Mach 0.8 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Surface skin friction, boundary layer profiles and turbulent intensity due to axially symmetric tangential slot injection into a transonic boundary layer were measured. Effects of slot height, multiple slot injection, and injection mass flow rate on the surface skin friction downstream of the the slot have been investigated. Surface skin friction was a function of the injection mass flow rate for x/s 40. Large normal pressure gradient and relatively large turbulent intensity were found near the slot with small injection mass flow rate; the region the high turbulent intensity moved downstream with increasing injection mass flow rate. The results with two slot injections indicated that the distance between slots should be less than 30 slot heights in order to achieve some benefits from the first slot. Of significant importance in the present investigation is that the skin friction reduction obtained at transonic speed is of the same order as obtained in the hypersonic regime. Additional work is required in order to formulate a correlation between the turbulent intensity and the injection mass flow rate that may be used in future analysis.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2694
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    NASA TECHNICAL REPORTS
  • 7
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    Theoretical investigation of crossflow effects on compressible turbulent boundary layer over bodies of revolution (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Crossflow effects on compressible turbulent boundary layer over bodies of revolution
    Keywords: AERODYNAMICS
    Type: NASA-CR-108939 , F-69-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    An experimental investigation of hypersonic turbulent boundary layers in adverse pressure gradient. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic turbulent boundary layer in adverse pressure gradients studied for transition, measuring static/pitot pressure, stagnation temperature and heat transfer rates
    Keywords: FLUID MECHANICS
    Type: AIAA PAPER 68-44 , AEROSPACE SCIENCES MEETING; Jan 22, 1968 - Jan 24, 1968; NEW YORK, NY
    Format: text
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  • 9
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    Crossflow effects on compressible turbulent boundary layer over bodies of revolution (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Compressible turbulent boundary layer with adverse pressure gradients and crossflow over revolving bodies, integrating numerically three dimensional compressible integral equations
    Keywords: FLUID MECHANICS
    Type: ISRAEL ANNUAL CONFERENCE ON AVIATION AND ASTRONAUTICS; Mar 04, 1970 - Mar 05, 1970; TEL AVI; ISRAEL
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  • 10
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    An experimental investigation of hypersonic turbulent boundary layers in adverse pressure gradient. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic turbulent boundary layer in adverse pressure gradients studied for transition, measuring static/pitot pressure, stagnation temperature and heat transfer rates
    Keywords: FLUID MECHANICS
    Type: AIAA PAPER 68-44 , ; ADEMIE DES SCIENCES|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING; Jan 22, 1968 - Jan 24, 1968; NEW YORK, NY
    Format: text
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