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  • 1
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    Protuberance heating test program (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented of the protuberance heating test program. Four general protuberance shapes on a flat plate were tested. Presentation and evaluation of the data both on the protuberance and in the wake regions are made. The test program is an extension of the general protuberance heat transfer test. The additional series of tests was conducted to define the extent of wake heating and to assess the effects of Reynolds number variation on heating both on and around the protuberances. The protuberance models were mounted near the forward end of a six-foot instrumented test plate with stringers that simulated interstage and skirt structure of the Saturn S-4B stage. The tests were performed at Mach numbers of 2.49, 3.51, and 4.44. Reynolds numbers per foot of 3 million and 1.5 million were used for the two lower Mach numbers and 3 million for a Mach number of 4.44. The test Mach numbers simulated the Saturn S-4B flight conditions during the most severe aerodynamic heating period. The test Reynolds numbers were somewhat higher than the flight values, but lower values could not be used because of tunnel and instrumentation limitations. Oil flow runs were made on two representative models at various combinations of Mach number and Reynolds number to help define the extent of wake heating.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-128400 , SM-47497
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An evaluation of Orbital Workshop passive thermal control surfaces (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The optical properties of selected Orbital Workshop thermal control surfaces are discussed from the time of their installation through the end of the Skylab missions. The surfaces considered are the goldized Kapton tape on the habitation area sidewall, the S-13G white paint on the Workshop aft skirt, and the multilayer insulation system on the forward dome of the habitation area. A quantitative assessment of the effects of exposure to the ascent and orbital environments is made including the effects of rocket exhaust plume contamination. Although optical property degradation of the external surfaces was noted, satisfactory thermal performance was maintained throughout the Skylab missions.
    Keywords: BIOTECHNOLOGY
    Type: ASME PAPER 74-ENAS-39 , Intersociety Conference on Environmental Systems; Jul 29, 1974 - Aug 01, 1974; Seattle, WA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Rain erosion considerations for launch vehicle insulation systems (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In recent years the Delta launch vehicle has incorporated the capability to be launched through rain. This capability was developed to eliminate a design constraint which could result in a costly launch delay. This paper presents the methodology developed to implement rain erosion protection for the insulated exterior vehicle surfaces. The effect of the interaction between insulation material rain erosion resistance, rainstorm models, surface geometry and trajectory variations is examined. It is concluded that rain erosion can significantly impact the performance of launch vehicle insulation systems and should be considered in their design.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME PAPER 77-ENAS-15 , Intersociety Conference on Environmental Systems; Jul 11, 1977 - Jul 14, 1977; San Francisco, CA; US
    Format: text
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  • 4
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    Simulation of non-continuum free jet plume impingement. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Noncontinuum free jet plume impingement simulation, effect of total temperature to model surface temperature ratio, Knudsen number and total enthalpy
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 68-237 , FLIGHT TEST, SIMULATION AND SUPPORT CONFERENCE; Mar 25, 1968 - Mar 27, 1968; LOS ANGELES, CA
    Format: text
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    NASA TECHNICAL REPORTS
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