Search Results - Beckwith, Ivan E.

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  1. 1
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    An accurate and rapid method for the design of supersonic nozzles / by Beckwith, Ivan E.

    Published 1955
    Government Document Book

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  2. 2
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    The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section / by Beckwith, Ivan E.

    Published 1952
    Government Document Book

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  3. 3
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    Heat transfer and skin friction by an integral method in the compressible laminar boundary layer with a streamwise pressure gradient / by Beckwith, Ivan E.

    Published 1953
    Government Document Book

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  4. 4
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    Heat transfer and recovery temperatures on a sphere with laminar, transitional, and turbulent boundary layers at Mach numbers of 2.00 and 4.15 / by Beckwith, Ivan E.

    Published 1957
    Government Document Book

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  5. 5
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    Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling / by Beckwith, Ivan E.

    Published 1958
    Government Document Book

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  6. 6
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    Local heat transfer and recovery temperatures on a yawed cylinder at a mach number of 4.15 and high Reynolds numbers / by Beckwith, Ivan E.

    Published 1961
    Government Document Book

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  7. 7
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    Similarity solutions for small cross flows in laminar compressible boundary layers / by Beckwith, Ivan E.

    Published 1961
    Government Document Book

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  8. 8
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    Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling / by Beckwith, Ivan E.

    Published 1959
    Government Document Book

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  9. 9
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    Görtler vortices and transition in wall boundary layers of two Mach 5 nozzles / by Beckwith, Ivan E.

    Published 1981
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    Government Document Book

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  10. 10
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    Detailed description and results of a method for computing mean and fluctuating quantities in turbulent boundary layers / by Beckwith, Ivan E., Bushnell, Dennis M.

    Published 1968
    Online Access
    Government Document eBook

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  11. 11
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    The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section / by Beckwith, Ivan E., Ridyard, Herbert W., Cromer, Nancy

    Published 1952
    Online Access
    Government Document eBook

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  12. 12
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    An accurate and rapid method for the design of supersonic nozzles / by Beckwith, Ivan E., Moore, J. A. (John Arnold)

    Published 1955
    Online Access
    Government Document eBook

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  13. 13
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    Compressible laminar boundary layer over a yawed infinite cylinder with heat transfer and arbitrary Prandtl number / by Reshotko, Eli

    Published 1957
    Other Authors: “…Beckwith, Ivan E.…”
    Government Document Book

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  14. 14
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    Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel /

    Published 1983
    Other Authors: “…Beckwith, Ivan E.…”
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  15. 15
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    Investigation of the flow through a single-stage two-dimensional nozzle in the Langley 11-inch hypersonic tunnel / by McLellan, Charles H.

    Published 1950
    Other Authors: “…Beckwith, Ivan E.…”
    Government Document Book

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  16. 16
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    Effects of a modified leading edge on noise and boundary-layer transition in a rod-wall sound shield at mach 5 / by Creel, Theodore R.

    Published 1981
    Other Authors: “…Beckwith, Ivan E.…”
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  17. 17
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    Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel by Creel, Theodore R.

    Published 1985
    Other Authors: “…Beckwith, Ivan E.…”
    Government Document Microfilm Book

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  18. 18
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    Noise reduction in a Mach 5 wind tunnel with a rectangular rod-wall sound shield / by Creel, Theodore R.

    Published 1980
    Other Authors: “…Beckwith, Ivan E.…”
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  19. 19
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    Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise / by Chen, Fang-Jenq

    Published 1984
    Other Authors: “…Beckwith, Ivan E.…”
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