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  • THERMODYNAMICS AND COMBUSTION  (231)
  • FLUID MECHANICS  (224)
  • 1970-1974  (455)
  • 1935-1939
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  • 1
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    Stagnation region heating of a phenolic-nylon ablator during return from planetary missions (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a stagnation-line analysis of the radiative heating of a phenolic-nylon ablator are reported. The analysis includes flowfield coupling with the ablator surface, equilibrium chemistry, multicomponent or binary diffusion and a coupled line and continuum radiation calculations. Users manual and operating instructions for the computer programs listed in the report are included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-112026
    Format: application/pdf
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  • 2
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    Formulation, derivation and development of the analysis of the interaction of ablating protection systems and stagnation region heating (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conservation equations for analysis of interaction of ablating protection systems and stagnation region heating
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-66931 , NASA-RFL-TR-70-1
    Format: application/pdf
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  • 3
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Eddy viscosity distributions in a Mach 20 turbulent boundary layer (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Shear stress and eddy viscosity distribution in Mach 20 compressible turbulent boundary layer, using mixing length flow theory
    Keywords: FLUID MECHANICS
    Type: ; IENCES (
    Format: text
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  • 5
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    Calculation of compressible adverse pressure gradient turbulent boundary layers. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Difficulties encountered in computing profile shapes in supersonic turbulent boundary layers with large pressure gradients, which result from a disagreement between data and theory, are investigated. Possible reasons given by various authors for this disagreement are discussed. Initial results seem to indicate that conventional reasons do not account for the observed difficulties. However, inclusion of the effect of curvature upon turbulent mixing has brought an improvement in calculations. Possible three-dimensional effects are also examined.
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 10; Feb. 197
    Format: text
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  • 6
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    Development status of reusable nonmetallic thermal protection (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Development of reusable oxidation resistant carbon-carbon laminates and surface insulation materials for thermal protection systems
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 1-38
    Format: text
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  • 7
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    Nonlinear least squares - An aid to thermal property determination. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Nonlinear least squares techniques can be used to determine effective thermal conductivity values from experimental data. Comparisons between measured and predicted conductivity values indicate that the analytically determined values can be used with confidence in performing thermal protection system analyses. A study was performed to compare the relative efficiencies of different minimizing techniques; the method of Peckham was the most efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
    Format: text
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  • 8
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    Calculation of transitional boundary-layer flows. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The results of a finite-difference calculation of hypersonic transitional boundary-layer flow are presented. Precursor-transition and low Reynolds number turbulence effects are included. These calculation results are compared with data from a source where profiles are available at the beginning, middle and end of the hypersonic transitional flow. The results indicate that the low Reynolds number effect is the most important.
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 11; Apr. 197
    Format: text
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  • 9
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    A local eddy viscosity model for turbulent shear flow (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In the model described, the eddy viscosity is assumed to be a fluid property dependent on the state of the fluid locally, namely the local density, turbulent kinetic energy, turbulence scale, and Mach number. An empirical law was found which related eddy viscosity to these properties satisfactorily for free jets. This law is used without modification for a set of test cases in free shear layers, free-jet decay, coaxial mixing, and wakes. The scale of turbulence is taken as a constant at any axial location equal to the width of the shear layer. By utilizing the boundary-layer order-of-magnitude analysis, a coupled set of fluid dynamic equations is formulated, which of necessity includes the equation for the production of turbulent kinetic energy.
    Keywords: FLUID MECHANICS
    Type: NASA. Langley Res. Center Free Turbulent Shear Flows, Vol. 1; p 529-547
    Format: application/pdf
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  • 10
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    A rational approach to the use of Prandtl's mixing length model in free turbulent shear flow calculations (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Prandtl's basic mixing length model was used to compute 22 test cases on free turbulent shear flows. The calculations employed appropriate algebraic length scale equations and single values of mixing length constant for planar and axisymmetric flows, respectively. Good agreement with data was obtained except for flows, such as supersonic free shear layers, where large sustained sensitivity changes occur. The inability to predict the more gradual mixing in these flows is tentatively ascribed to the presence of a significant turbulence-induced transverse static pressure gradient which is neglected in conventional solution procedures. Some type of an equation for length scale development was found to be necessary for successful computation of highly nonsimilar flow regions such as jet or wake development from thick wall flows.
    Keywords: FLUID MECHANICS
    Type: Free Turbulent Shear Flows, Vol. 1; p 67-137
    Format: application/pdf
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