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  • 1
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    Real gas effects on hypersonic boundary-layer stability (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: High-temperature effects alter the physical and transport properties of a gas, air in particular, due to vibrational excitation and gas dissociation, and thus the chemical reactions have to be considered in order to compute the flow field. Linear stability of high-temperature boundary layers is investigated under the assumption of chemical equilibrium and this gas model is labeled here as real gas model. In this model, the system of stability equations remains of the same order as for the perfect gas and the effect of chemical reactions is introduced only through mean flow and gas property variations. Calculations are performed for Mach 10 and 15 boundary layers and the results indicate that real gas effects cause the first mode instability to stabilize while the second mode is made more unstable. It is also found that the second mode instability shifts to lower frequencies. There is a slight destabilizing influence of real gas on the Goertler instability as compared to the perfect gas results.
    Keywords: AERODYNAMICS
    Type: Physics of Fluids A (ISSN 0899-8213); 3; 803-821
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  • 2
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    Numerical solution of the steady-state Navier-Stokes equations for hypersonic flow about blunt axisymmetric bodies (1976)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The steady-state Navier-Stokes equations are solved for hypersonic flow about blunt axisymmetric bodies. The equations of motion are solved by successive approximations using an implicit finite-difference scheme. The results are compared with viscous shock-layer theory, experimental data, and time-dependent solutions of the Navier-Stokes equations. It is demonstrated that viscous shock-layer theory is sufficiently accurate for the range of flight conditions normally encountered by entry vehicles.
    Keywords: AERODYNAMICS
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  • 3
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    Geometric shape factors for planetary-thermal and planetary-reflected radiation incident upon spinning and nonspinning spacecraft (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Geometric factors for planetary thermal and reflected radiation on spinning and nonspinning spacecraft
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-2835
    Format: application/pdf
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  • 4
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    Aerodynamic design of the contoured wind-tunnel liner for the NASA supercritical, laminar-flow-control, swept-wing experiment (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An overview is presented of the entire procedure developed for the aerodynamic design of the contoured wind tunnel liner for the NASA supercritical, laminar flow control (LFC), swept wing experiment. This numerical design procedure is based upon the simple idea of streamlining and incorporates several transonic and boundary layer analysis codes. The liner, presently installed in the Langley 8 Foot Transonic Pressure Tunnel, is about 54 ft long and extends from within the existing contraction cone, through the test section, and into the diffuser. LFC model testing has begun and preliminary results indicate that the liner is performing as intended. The liner design results presented in this paper, however, are examples of the calculated requirements and the hardware implementation of them.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2335 , L-15521 , NAS 1.60:2335
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  • 5
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    Vorticity interaction effects on blunt bodies (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Numerical solutions of the viscous shock layer equations governing laminar and turbulent flows of a perfect gas and radiating and nonradiating mixtures of perfect gases in chemical equilibrium are presented for hypersonic flow over spherically blunted cones and hyperboloids. Turbulent properties are described in terms of the classical mixing length. Results are compared with boundary layer and inviscid flowfield solutions; agreement with inviscid flowfield data is satisfactory. Agreement with boundary layer solutions is good except in regions of strong vorticity interaction; in these flow regions, the viscous shock layer solutions appear to be more satisfactory than the boundary layer solutions. Boundary conditions suitable for hypersonic viscous shock layers are devised for an advanced turbulence theory.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2778 , DCW-R-08-01
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  • 6
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    A study of the aerothermal environment for the Pioneer Venus multiprobe mission (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In December 1978, four Pioneer Venus probe spacecraft are scheduled for almost simultaneous entry into the Venusian atmosphere at widely dispersed points about the planet. In this study, both detailed and approximate flow field analyses are used to define the entry aerothermal environment for the forebody of each of the four probes. The results show that approximate analyses can be used to predict inviscid radiative and laminar convective heating rates with acceptable accuracy. However, the radiative heating rates obtained with inviscid analyses are significantly greater than those obtained with a nonablating viscous-shock-layer (VSL) analysis, because the VSL analysis includes a strongly absorbing boundary layer. Also, the results show that the radiative heating is sensitive to small variations in atmospheric gas composition while the convective heating is not affected. With carbon-phenolic injection, the convective heating is reduced substantially while the overall radiative heating reduction is very small. Most of the radiative blockage occurs in the atomic line transitions which is significant only in the stagnation region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 77-766 , Thermophysics Conference; Jun 27, 1977 - Jun 29, 1977; Albuquerque, NM
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  • 7
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    Nonreacting and equilibrium chemically reacting turbulent boundary-layer flows (1971)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Nonreacting and equilibrium chemically reacting gas turbulent boundary layer flows through hypervelocity nozzles, comparing calculation with experiment
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 71-597 , FLUID AND PLASMA DYNAMICS CONFERENCE; Jun 21, 1971 - Jun 23, 1971; PALO ALTO, CA
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  • 8
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    The impact of turbulence on a radiating shock layer with coupled ablation injection (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper provides a description of the potential impact of turbulence on a radiating flow field with large surface blowing. This is accomplished by calculating the forebody flow field with coupled carbon-phenolic mass injection for a probe entering the Jupiter atmosphere. Both laminar and turbulent flow conditions are assumed. For the no blowing solutions, turbulence is shown to have no impact on the surface radiative heating. However, with ablation injection, turbulence significantly increases the surface radiative heating rate. This occurs because the turbulence brings the high temperature gases closer to the surface, thus thinning the cool molecular gases at the wall which are responsible for blocking much of the radiation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1186 , Fluid and Plasma Dynamics Conference; Jul 10, 1978 - Jul 12, 1978; Seattle, WA
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  • 9
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    Turbulent viscous-shock-layer solutions with strong vorticity interaction (1976)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Numerical solutions of the viscous-shock-layer equations governing laminar and turbulent flows of a perfect gas and radiating and nonradiating mixtures of perfect gases in chemical equilibrium are presented for hypersonic flow over spherically blunted cones and hyperboloids. The results are compared with boundary-layer and inviscid flow-field solutions. The agreement with the inviscid flow field data is satisfactory. The agreement with boundary-layer solutions is good except in regions of strong vorticity interaction. In these flow regions, the viscous-shock-layer solutions appear to be more satisfactory than the boundary-layer solutions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-120 , Aerospace Sciences Meeting; Jan 26, 1976 - Jan 28, 1976; Washington, DC
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  • 10
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    Viscous-shock-layer solutions with radiation and ablation injection for Jovian entry (1975)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper presents results that describe the flow field and surface response conditions for a planetary probe entering the atmosphere of Jupiter. The results are obtained with a viscous-shock-layer analysis which includes mass injection, radiative transfer, diffusion, and viscous effects. Radiative transfer is calculated with an existing nongray radiation model that accounts for molecular band, atomic line, and continuum transitions. Particular emphasis is given to the effect of mass injection on the stagnation and downstream flow. Results for both specified and coupled mass injection are obtained for a carbon heat shield.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-671 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; May 27, 1975 - May 29, 1975; Denver, CO
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