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  • 1
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    Viscous shock layer analysis of the Martian aerothermal environment (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 5; p. 633-640.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Outer planet entry probes aerothermal environment - Status of prediction methodology (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A description is given of the computational codes that are to be used in studies of the heating and aerodynamic performance of entry probes for the scientific exploration of the planets Jupiter, Saturn, and Uranus. These codes include a time-asymptotic numerical method which takes into account radiative transport and equilibrium chemistry for the direct solution of the radiative, inviscid flow over an axisymmetric or two-dimensional body. The method considers both supersonic and subsonic flow in the downstream region. Another code represents a laminar, viscous-shock-layer solution.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: AIAA PAPER 75-1148 , American Institute of Aeronautics and Astronautics and American Geophysical Union, Conference on the Exploration of the Outer Planets; Sept. 17-19, 1975; St. Louis, MO
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  • 3
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    A viscous-shock-layer analysis of the Martian aerothermal environment (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Surface heating and flow field results for the stagnation region of a planetary exploration vehicle entering the Martian atmosphere are presented. Solutions for the high-energy viscous flow fields with complete radiative heating are derived from a viscous-shock-layer analysis for laminar flow under chemical equilibrium conditions. Results are shown with and without coupled radiation ablation injection utilizing the recently developed curve fits for the transport and thermodynamic properties of Martian atmospheric and ablation species. This analysis includes a strongly absorbing boundary layer and, therefore, gives much lower radiative heat transfer rates than those obtained from inviscid analyses.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: AIAA PAPER 91-1345
    Format: text
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  • 4
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    An investigation of the effects of mass loss, shape change and real gas aerodynamics on a Jovian atmospheric reconstruction experiment (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A survey of the effects of mass loss, shape change and real-gas aerodynamics on a Jovian atmospheric reconstruction experiment is carried out. Techniques used to reconstruct atmospheric profiles from entry probe measurements are discussed and some of the parameters which affect their accuracy are identified. Trajectory analyses and real-gas, radiatively-coupled flow field analyses (which include the effects of mass loss and shape change) are carried out for several candidate probe configurations. From these analyses, uncertainties in the atmospheric reconstruction procedure are estimated. Finally, the prospects for reducing these uncertainties by optimizing probe configuration and by instrumentation of the probe heat shield to measure actual shape change are considered.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: IAF PAPER 76-073 , International Astronautical Congress; Oct 10, 1976 - Oct 16, 1976; Anaheim, CA
    Format: text
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  • 5
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    Direct Monte Carlo Simulations of Hypersonic Low-Density Flows about an ASTV Including Wake Structure (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results of a numerical study concerning flow past a 70-deg blunted cone in hypersonic low-density flow environments are presented using the direct simulation Monte-Carlo method. The flow conditions simulated are those that can be obtained in existing low-density hypersonic wind tunnels. Results indicate that a stable vortex forms in the near wake at and below a freestream Knudsen number (based on cone diameter) of 0.01 and the size of the vortex increases with decreasing Knudsen number. The base region of the flow remains in thermal nonequilibrium for all cases considered herein.
    Keywords: Aerodynamics
    Type: NASA-TM-111529 , NAS 1.15:111529
    Format: application/pdf
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  • 6
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    Review of blunt body wake flows at hypersonic low density conditions (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Recent results of experimental and computational studies concerning hypersonic flows about blunted cones including their near wake are reviewed. Attention is focused on conditions where rarefaction effects are present, particularly in the wake. The experiments have been performed for a common model configuration (70 deg spherically-blunted cone) in five hypersonic facilities that encompass a significant range of rarefaction and nonequilibrium effects. Computational studies using direct simulation Monte Carlo (DSMC) and Navier-Stokes solvers have been applied to selected experiments performed in each of the facilities. In addition, computations have been made for typical flight conditions in both Earth and Mars atmospheres, hence more energetic flows than produced in the ground-based tests. Also, comparisons of DSMC calculations and forebody measurements made for the Japanese Orbital Reentry Experiment (OREX) vehicle (a 50 deg spherically-blunted cone) are presented to bridge the spectrum of ground to flight conditions.
    Keywords: Aerodynamics
    Type: NASA-TM-111599 , NAS 1.15:111599 , AIAA Paper 96-1803 , AIAA ThermophysicS Conference; Jun 17, 1996 - Jun 20, 1996; New Orleans, LA; United States
    Format: application/pdf
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