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  • 1
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    Convective and radiative heating of a Saturn entry probe (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The extent of convective and radiative heating for a Saturn entry probe is investigated in the absence and presence of ablation mass injection. The flow in the shock layer is assumed to be axisymmetric, viscous and in local thermodynamic equilibrium. The importance of chemical nonequilibrium effects for both the radiative and convective nonblowing surface heating rates is demonstrated for prescribed entry conditions. Results indicate that the nonequilibrium chemistry can significantly influence the rate of radiative heating to the entry probes. With coupled carbon-phenolic ablation injection, the convective heating rates are reduced substantially. Turbulence has little effect on radiative heating but it increases the convective heating considerably.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: International Journal of Heat and Mass Transfer (ISSN 0017-9310); 27; 191-205
    Format: text
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  • 2
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    Comparison of Euler and full potential marching techniques for flows over complex configurations (1986)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Two recently developed aerodynamic prediction techniques based on the steady full potential equation and the unsteady Euler equations have been applied to a variety of three-dimensional supersonic flow problems exhibiting embedded subsonic regions. Both techniques utilize planar Gauss-Seidel relaxation in the marching direction and approximate factorization in the cross-flow plane. A conservative switching scheme and flux bias technique are employed in the full potential method to transition from the supersonic marching procedure to a subsonic relaxation algorithm and vice versa. A new unified approach with finite volume, high accuracy (up to third order) Total Variation Diminishing formulation (based on Roe's scheme) is used in the Euler solver. In the supersonic regions of the flow an 'infinitely large' time step is employed, and a finite time step is applied in the subsonic regions of the flow to reach the steady-state as a time-asymptote. Numerical solutions are obtained for a number of complex configurations, including: (1) an elliptic waverider, (2) a realistic fighter configuration, (3) the Space Shuttle, and (4) a Shuttle-like configuration. Both the Full Potential and Euler numerical results are in good agreement with available experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0244
    Format: text
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  • 3
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    Nonlinear potential analysis techniques for supersonic aerodynamic design (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A numerical method based on the conservation form of the full potential equation has been applied to the problem of three-dimensional supersonic flows with embedded subsonic regions. The governing equation is cast in a nonorthogonal coordinate system, and the theory of characteristics is used to accurately monitor the type-dependent flow field. A conservative switching scheme is employed to transition from the supersonic marching procedure to a subsonic relaxation algorithm and vice versa. The newly developed computer program can handle arbitrary geometries with fuselage, canard, wing, flow through nacelle, vertical tail and wake components at combined angles of attack and sideslip. Results are obtained for a variety of configurations that include a Langley advanced fighter concept with fuselage centerline nacelle, Rockwell's Advanced Tactical Fighter (ATF) with wing mounted nacelles, and the Shuttle Orbiter configuration. Comparisons with available experiments were good.
    Keywords: AERODYNAMICS
    Type: NASA-CR-172507 , NAS 1.26:172507
    Format: application/pdf
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  • 4
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    Nonlinear computation of wing-body-vertical tail-wake flows at low supersonic speeds (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A numerical method based on the conservation form of the full potential equation has been applied to the problem of three-dimensional supersonic flows with embedded subsonic regions. The governing equation is cast in a nonorthogonal coordinate system, and the theory of characteristics is used to accurately monitor the type-dependent flow field. A conservative switching scheme is employed to transition from the supersonic marching procedure to a subsonic relaxation algorithm and vice versa. The newly developed computer program can handle arbitrary geometries with fuselage, wing, vertical tail and wake components at combined angle of attack and sideslip. Results are presented for a low supersonic Mach numbers flow over the Shuttle orbiter (including the OMS pods and vertical tail), and for flows over a realistic fighter type configuration. Comparisons with experimental data are shown to be in good agreement for various cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0427
    Format: text
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  • 5
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    Treatment of supersonic flows with embedded subsonic regions (1985)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 41-48
    Format: text
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  • 6
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    Application of a two-dimensional grid solver for three-dimensional problems (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A two-dimensional elliptic grid solver is presented and its application to various three-dimensional configurations, both internal and external, is demonstrated. The method uses proper forcing terms to cluster grid points near boundaries with a specified grid spacing and allows grid lines to intersect the boundaries at a specified angle. By segmenting the region, grid results are generated for sharp leading edged configurations and wing-vertical tail combinations.
    Keywords: AERODYNAMICS
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  • 7
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    Effects of precursor heating on chemical and radiative nonequilibrium viscous flow around a Jovian entry body (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The influence of precursor heating on viscous chemical nonequilibrium radiating flow around a Jovian entry body is investigated. Results obtained for a 45 deg hyperboloid blunt body entering the Jupiter's nominal atmosphere at zero angle of attack indicate that the nonequilibrium radiative heating rate is significantly higher than the corresponding equilibrium heating. The precursors heating, in general, increases the radiative and convective heating to the body and this increase is slightly higher for the nonequilibrium conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-907 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
    Format: text
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  • 8
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    Influence of precursor heating on viscous flow around a Jovian entry body (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The influence of changes in precursor region flow properties (resulting from the absorption of radiation from the shock layer) on the entire shock layer flow phenomena is investigated. Axially symmetric case is considered for both the preheating zone (precursor region) and shock layer. The flow in the shock layer is considered to be viscous with chemical equilibrium but radiative nonequilibrium. Realistic thermo-physical and spectral models are employed and results are obtained by implicit finite difference and iterative procedures. The results indicate that precursor heating increases the radiative heating of the body by a maximum of 7.5% for a 116 KM entry conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-190 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
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  • 9
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    A conservative type-dependent full potential method for the treatment of supersonic flows with embedded subsonic regions (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A nonlinear method based on the full potential equation in conservation form, cast in an arbitrary coordinate system, has been developed to treat predominantly supersonic flows with embedded subsonic regions. This type of flow field occurs frequently near the fuselage-canopy junction area and wing leading edge regions for a moderately swept fighter configuration. The method uses the theory of characteristics to accurately monitor the type-dependent flow field. A conservative switching scheme is developed to transition from the supersonic marching algorithm to a subsonic relaxation procedure, and vice versa. An implicit approximate factorization scheme is employed to solve the finite-differenced equation. Results are shown for a few configurations, including a wing-body-wake realistic fighter model having embedded subsonic regions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1887 , Computational Fluid Dynamics Conference; Jul 13, 1983 - Jul 15, 1983; Danvers, MA
    Format: text
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  • 10
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    Nonequilibrium viscous flow over Jovian entry probes at high altitudes (1979)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The viscous chemical nonequilibrium flow around a Jovian entry body is investigated at high altitudes using two different methods. First method is only for the stagnation region and integrates the full Navier-Stokes equations from the body surface to the freestream. The second method uses viscous shock layer equations between the body surface and the shock. Due to low Reynolds numbers, both methods use surface slip boundary conditions and the second method also uses shock slip boundary conditions. The results of the two methods are compared at the stagnation point. It is found that the entire shock layer is under chemical nonequilibrium at higher altitudes and that the slip boundary conditions are important at these altitudes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1079 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Jun 04, 1979 - Jun 06, 1979; Orlando, FL
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