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  1. 1
    A dual-cooled hydrogen-oxygen rocket engine heat transfer analysis

    A dual-cooled hydrogen-oxygen rocket engine heat transfer analysis by Kacynski, Kenneth John

    Published 1991
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  2. 2
    7.5K lbf thrust engine preliminary design for orbit transfer vehicle task D.5 final report /

    7.5K lbf thrust engine preliminary design for orbit transfer vehicle task D.5 final report / by Hayden, Warren R.

    Published 1994
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  3. 3
    Space station hydrogen/oxygen thruster technology /

    Space station hydrogen/oxygen thruster technology / by Briley, G. L.

    Published 1988
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  4. 4
    Retardation analytical model to extend service life monthly technical progress narrative, month of August 1984 /

    Retardation analytical model to extend service life monthly technical progress narrative, month of August 1984 / by Matejczyk, Daniel E., 1956-

    Published 1984
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  5. 5
    The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios

    The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios by Kacynski, Kenneth J.

    Published 1994
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  6. 6
    Turbine blade thermal fatigue testing Pratt and Whitney aircraft hollow core blades

    Turbine blade thermal fatigue testing Pratt and Whitney aircraft hollow core blades by Ingram, Jeff

    Published 1985
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  7. 7
    Space Transportation Booster Engine (STBE) configuration study second quarterly review.

    Space Transportation Booster Engine (STBE) configuration study second quarterly review.

    Published 1986
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  8. 8
    A transient model of the RL10A-3-3A rocket engine

    A transient model of the RL10A-3-3A rocket engine by Binder, Michael P.

    Published 1995
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  9. 9
    Determination of the relative resistance to ignition of selected turbopump materials in high-pressure, high-temperature, oxygen environments test report.

    Determination of the relative resistance to ignition of selected turbopump materials in high-pressure, high-temperature, oxygen environments test report.

    Published 1986
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  10. 10
    Design, fabrication, and test of the RL10 derivative II chamber/primary nozzle

    Design, fabrication, and test of the RL10 derivative II chamber/primary nozzle by Marable, R. W.

    Published 1989
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  11. 11
    Dual-throat thruster thermal model final report /

    Dual-throat thruster thermal model final report / by Ewen, R. L.

    Published 1986
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  12. 12
    Integrated hydrogen-oxygen technology applied to auxilliary propulsion systems final report /

    Integrated hydrogen-oxygen technology applied to auxilliary propulsion systems final report /

    Published 1990
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  13. 13
    A unique high heat flux facility for testing hypersonic engine components

    A unique high heat flux facility for testing hypersonic engine components by Melis, Matthew E.

    Published 1990
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  14. 14
    Predicted performance of an integrated modular engine system

    Predicted performance of an integrated modular engine system by Binder, Michael P.

    Published 1993
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  15. 15
    NASA flow field analysis final report /

    NASA flow field analysis final report / by Merkle, C. L. (Charles L.)

    Published 1996
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  16. 16
    Hydrogen-oxygen torch ignitor /

    Hydrogen-oxygen torch ignitor / by Repas, George A.

    Published 1994
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  17. 17
    Qualitative flow visualization of a 110-N hydrogen/oxygen laboratory model thruster

    Qualitative flow visualization of a 110-N hydrogen/oxygen laboratory model thruster by De Groot, Wim A. (Wim Adrianus), 1954-

    Published 1997
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  18. 18
    Performance comparison of axisymmetric and three-dimensional hydrogen film coolant injection in a 110N hydrogen/oxyen rocket

    Performance comparison of axisymmetric and three-dimensional hydrogen film coolant injection in a 110N hydrogen/oxyen rocket by Arrington, Lynn A.

    Published 1992
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  19. 19
    Highly Evolved Expendable Launch Vehicle (HEELV) for the HRST program final report, contract H27831D, W-6-PP-02996.

    Highly Evolved Expendable Launch Vehicle (HEELV) for the HRST program final report, contract H27831D, W-6-PP-02996.

    Published 1997
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