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  • 1
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    Unknown
    Space shuttle solid rocket booster sting interference wind tunnel test analysis (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel test results from shuttle solid rocket booster (SRB) sting interference tests were evaluated, yielding the general influence of the sting on the normal force and pitching moment coefficients and the side force and yawing moment coefficients. The procedures developed to determine the sting interference, the development of the corrected aerodynamic data, and the development of a new SRB aerodynamic mathematical model are documented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-161885 , TR-230-2042
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Solid rocket booster sting interference wind tunnel test analysis, appendix D (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Additional analyses of wind tunnel test results from SRB sting interference test TWT 660 and HRWT 042 were conducted to evaluate the sting interference that may be present in the Space Shuttle SRB reentry aerodynamic math model. Additional wind tunnel data was obtained at higher angles of attack from test program TWT 660 and test program HRWT 042. The additional data were analyzed to evaluate the procedures used to fair the data in the development of the SRB reentry aerodynamic data Tape no. 5.
    Keywords: AERODYNAMICS
    Type: NASA-CR-162084 , NAS 1.26:162082 , TR-230-2042-A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Space shuttle plume/simulation application (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of pressure and strain-gage data from space shuttle wind tunnel test IA119 and IA138 was performed to define the influence on aerodynamic characteristics resulting from the main propulsion system and solid rocket booster plumes. Aerodynamic characteristics of each of the elements, the components and total vehicle of the space shuttle vehicle during ascent flight was considered. Pressure data were obtained over the aft portions of the space shuttle wind tunnel model in addition to wing and elevon gage data.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-161275 , TR-230-1964
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Space shuttle plume/simulation application: Results and math model supersonic data (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analysis of pressure and gage wind tunnel data from space shuttle wind tunnel test IA138 was performed to define the aerodynamic influence of the main propulsion system and solid rocket booster plumes on the total vehicles, elements, and components of the space shuttle vehicle during the supersonic portion of ascent flight. A math model of the plume induced aerodynamic characteristics was developed for a range of Mach numbers to match the forebody aerodynamic math model. The base aerodynamic characteristics are presented in terms of forces and moments versus attitude. Total vehicle base and forebody aerodynamic characteristics are presented in terms of aerodynamic coefficients for Mach numbers from 1.55 to 2.5.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-161274 , TR-230-1963
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Space shuttle plume simulation application. Results and math model (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Pressure and gauge wind tunnel data from a transonic test of a 0.02 scale model of the space shuttle launch vehicle was analyzed to define the aerodynamic influence of the main propulsion system and solid rocket booster plumes during the transonic portion of ascent flight. Air was used as a simulant gas to develop the model exhaust plumes. A math model of the plume induced aerodynamic characteristics was developed for a range of Mach numbers to match the forebody aerodynamic math model. The base aerodynamic characteristics are presented in terms of forces and moments versus attitude. Total vehicle base and forebody aerodynamic characteristics are presented in terms of aerodynamic coefficients for Mach number from 0.6 to 1.4 Element and component base and forebody aerodynamic characteristics are presented for Mach numbers of 0.6, 1.05, 1.1, 1.25 and 1.4. The forebody data is available at Mach 1.55. Tolerances for all plume induced aerodynamic characteristics are developed in terms of a math model.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-CR-150889
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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