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  • 1985-1989  (9)
  • 1
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    Overview of Aerothermodynamic Loads Definition Study (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-30
    Description: The Aerothermodynamic Loads Definition were studied to develop methods to more accurately predict the operating environment in the space shuttle main engine (SSME) components. Development of steady and time-dependent, three-dimensional viscous computer codes and experimental verification and engine diagnostic testing are considered. The steady, nonsteady, and transient operating loads are defined to accurately predict powerhead life. Improvements in the structural durability of the SSME turbine drive systems depends on the knowledge of the aerothermodynamic behavior of the flow through the preburner, turbine, turnaround duct, gas manifold, and injector post regions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 3-5
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Validation of viscous and inviscid computational methods for turbomachinery components (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An assessment of several three-dimensional computer codes used at the NASA Lewis Research Center is presented. Four flow situations are examined, for which both experimental data and computational results are available. The four flows form a basis for the evaluation of the computational procedures. It is concluded that transonic rotor flow at peak efficiency conditions may be calculated with a reasonable degree of accuracy, whereas, off-design conditions are not accurately determined. Duct flows and turbine cascade flows may also be computed with reasonable accuracy whereas radial inflow turbine flow remains a challenging problem.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-42
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Computation of three-dimensional, rotational flow through turbomachinery blade rows for improved aerodynamic design studies (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The performance of a three dimensional computer code developed for predicting the flowfield in stationary and rotating turbomachinery blade rows is described in this study. The four stage Runge-Kutta numerical integration scheme is used for solving the governing flow equations and yields solution to the full, three dimensional, unsteady Euler equations in cylindrical coordinates. This method is fully explicit and uses the finite volume, time marching procedure. In order to demonstrate the accuracy and efficiency of the code, steady solutions were obtained for several cascade geometries under widely varying flow conditions. Computed flowfield results are presented for a fully subsonic turbine stator and a low aspect ratio, transonic compressor rotor blade under maximum flow and peak efficiency design conditions. Comparisons with Laser Anemometer measurements and other numerical predictions are also provided to illustrate that the present method predicts important flow features with good accuracy and can be used for cost effective aerodynamic design studies.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 86-GT-26
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Validation of viscous and inviscid computational methods for turbomachinery components (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An assessment of several three-dimensional computer codes used at the NASA Lewis Research Center is presented. Four flow situations are examined, for which both experimental data and computational results are available. The four flows form a basis for the evaluation of the computational procedures. It is concluded that transonic rotor flow at peak efficiency conditions may be calculated with a reasonable degree of accuracy, whereas, off-design conditions are not accurately determined. Duct flows and turbine cascade flows may also be computed with reasonable accuracy whereas radial inflow turbine flow remains a challenging problem.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87193 , E-2765 , NAS 1.15:87193 , International Gas Turbine Conference; Dusseldorf; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Assessment of three-dimensional inviscid codes and loss calculations for turbine aerodynamic computations (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An assessment of several three dimensional inviscid turbine aerodynamic computer codes and loss models used at the NASA Lewis Research Center is presented. Five flow situations are examined, for which both experimental data and computational results are available. The five flows form a basis for the evaluation of the computational procedures. It was concluded that stator flows may be calculated with a high degree of accuracy, whereas, rotor flow fields are less accurately determined. Exploitation of contouring, leaning, bowing, and sweeping will require a three dimensional viscous analysis technique.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 84-GT-187 , ASME, Transactions, Journal of Engineering for Gas Turbines and Power (ISSN 0022-0825); 107; 265-275;
    Format: text
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  • 6
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    Analytical and physical modeling program for the NASA Lewis Research Center's Altitude Wind Tunnel (AWT) (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An effort is currently underway at the NASA Lewis Research Center to rehabilitate and extend the capabilities of the Altitude Wind Tunnel (AWT). This extended capability will include a maximum test section Mach number of about 0.9 at an altitude of 55,000 ft and a -20 F stagnation temperature (octagonal test section, 20 ft across the flats). In addition, the AWT will include an icing and acoustic research capability. In order to insure a technically sound design, an AWT modeling program (both analytical and physical) was initiated to provide essential input to the AWT final design process. This paper describes the modeling program, including the rationale and criteria used in program definition, and presents some early program results.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 85-0379
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Analytical modeling of circuit aerodynamics in the new NASA Lewis Altitude Wind Tunnel (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Rehabilitation and extention of the capability of the altitude wind tunnel (AWT) was analyzed. The analytical modelling program involves the use of advanced axisymmetric and three dimensional viscous analyses to compute the flow through the various AWT components. Results for the analytical modelling of the high speed leg aerodynamics are presented; these include: an evaluation of the flow quality at the entrance to the test section, an investigation of the effects of test section bleed for different model blockages, and an examination of three dimensional effects in the diffuser due to reentry flow and due to the change in cross sectional shape of the exhaust scoop.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0380
    Format: text
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  • 8
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    Analytical modeling of circuit aerodynamics in the new NASA Lewis wind tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Rehabilitation and extention of the capability of the altitude wind tunnel (AWT) was analyzed. The analytical modeling program involves the use of advanced axisymmetric and three dimensional viscous analyses to compute the flow through the various AWT components. Results for the analytical modeling of the high speed leg aerodynamics are presented; these include: an evaluation of the flow quality at the entrance to the test section, an investigation of the effects of test section bleed for different model blockages, and an examination of three dimensional effects in the diffuser due to reentry flow and due to the change in cross sectional shape of the exhaust scoop.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86912 , E-2405 , NAS 1.15:86912 , AIAA PAPER 85-0380 , Aerospace Sci. Meeting; Jan 14, 1985 - Jan 17, 1985; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Analytical and physical modeling program for the NASA Lewis Research Center's Altitude Wind Tunnel (AWT) (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An effort is currently underway at the NASA Lewis Research Center to rehabilitate and extend the capabilities of the Altitude Wind Tunnel (AWT). This extended capability will include a maximum test section Mach number of about 0.9 at an altitude of 55,000 ft and a -20 F stagnation temperature (octagonal test section, 20 ft across the flats). In addition, the AWT will include an icing and acoustic research capability. In order to insure a technically sound design, an AWT modeling program (both analytical and physical) was initiated to provide essential input to the AWT final design process. This paper describes the modeling program, including the rationale and criteria used in program definition, and presents some early program results.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-86919 , E-2413 , NAS 1.15:86919 , AIAA PAPER 85-0379 , Aerospace Sci. Meeting; Jan 14, 1985 - Jan 17, 1985; Reno, NV; United States
    Format: application/pdf
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