Influence of sonic-line location on Mars Pathfinder Probe aerothermodynamics

Gnoffo, Peter A.; Weilmuenster, K. J.; Braun, Robert D.; Cruz, Christopher I.

doi:10.2514/3.26737

Cited by 76 publications

(29 citation statements)

References 18 publications

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“…Finally, the CFD analysis of the MBS have been preceded by a code validation phase performed considering the available numerical and experimental data for the Mars Pathfinder probe at entry peak heating conditions, as summarized in ) (Gnoffo et al, 1998) (Gnoffo et al, 1996) (Mitcheltree et al, 1995).…”

Section: Freestream Conditionsmentioning

confidence: 99%

Fluid Dynamics Analysis of a Space Vehicle Entering the Mars Atmosphere

Viviani¹,

Pezzella²

2012

Applied Computational Fluid Dynamics

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Section: Freestream Conditionsmentioning

confidence: 99%

Fluid Dynamics Analysis of a Space Vehicle Entering the Mars Atmosphere

Viviani¹,

Pezzella²

2012

Applied Computational Fluid Dynamics

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“…LAURA is a computational fluid dynamics (CFD) tool specialized for hypersonic reentry physics and chemistry. In the past, the LAURA code has been applied and validated for a range of vehicle shapes and flow conditions including the Shuttle Orbiter laminar aerothermodynamic flight data 20 , blunt planetary configurations, 21,22 and slender lifting bodies. 23 The code is a three-dimensional upwind finite-volume solver for the inviscid Euler equations, thin-layer Navier-Stokes, or full Navier-Stokes governing equations.…”

Section: Computational Simulation Of Baseline Model Surface Flowmentioning

confidence: 99%

Turbulent Supersonic/Hypersonic Heating Correlations for Open and Closed Cavities

Everhart

Greene

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Supersonic/hypersonic laminar heating correlations that were developed for damageassessment analysis of atmospheric re-entry vehicles have been modified and extended to cover fully-turbulent conditions over rectangular cavity geometries that are aligned with the local velocity. Turbulent boundary layer properties were computationally determined and used to develop the cavity geometry parametrics and to correlate experimental closed cavity heating data to yield new relationships for the floor-averaged and centerline endwall peakheating augmentation. With the form of the closed-cavity correlations established, historical data were used to develop new correlations for turbulent open-cavity heating.

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“…The Mars atmosphere version of the code 7 contains an 8-species C O 2 ,N 2 c hemical-kinetics model. This is the same computational code used to make aerodynamic and heating predictions for Mars Path nder 8,11 . Aerodynamic predictions from the code have agreed well with Viking ight data 11 and been shown to be in excellent agreement with Mars Path nder ight data 12 .…”

Section: Entry Trajectoriesmentioning

confidence: 99%

Aerothermal heating predictions for Mars Microprobe

Mitcheltree

DiFulvio

Horvath

et al. 1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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A combination of computational predictions and experimental measurements of the aerothermal heating expected on the two Mars Microprobes during their entry to Mars are presented. The maximum, non-ablating, heating rate at the vehicle's stagnation point at = 0 0 is predicted for an undershoot trajectory to be 194 W=cm 2 with associated stagnation point pressure of 0.064 atm. Maximum stagnation point pressure occurs later during the undershoot trajectory and is 0.094 atm. From computations at seven overshoot-trajectory points, the maximum heat load expected at the stagnation point is near 8800 J=cm 2 . Heat rates and heat loads on the vehicle's afterbody are much lower than the forebody. At zero degree angle-of-attack, heating over much of the hemispherical afterbody is predicted to be less than 2 percent of the stagnation point v alue. Good qualitative agreement is demonstrated for forebody and afterbody heating between CFD calculations at Mars entry conditions and experimental thermographic phosphor measurements from the Langley 20-Inch Mach 6 Air Tunnel. A n o v el approach which incorporates six degree-of-freedom trajectory simulations to perform a statistical estimate of the e ect of angle-of-attack, and other o -nominal conditions, on heating is included. Nomenclature B = Ballistic coe cient, kg=m 2 C h = heat transfer coe cient M = Mach n umber P = pressure, atm q = heat rate, W=cm 2 R n = nose radius, m s = surface distance from geometric stagnation point, m t = independent v ariable time, s V = v elocity, m=s x; z = independent spatial dimensions, m = angle-of-attack, deg = side-slip angle, deg = density, kg=m 3 = standard deviation IntroductionWhen the Mars Surveyor 98 Lander is launched in January of 1999, it will transport not only its own lander to Mars, but two small soil penetrators. These Aerospace Engineer, Aerothermodynamics Branch, Aeroand Gas-Dynamics Division, NASA Langley Research Center, Senior member AIAA.y Aerospace Engineer, Aerothermodynamics Branch, Aeroand Gas-Dynamics Division, NASA Langley Research Center, Senior member AIAA.z Aerospace Engineer, Aerothermodynamics Branch, Aeroand Gas-Dynamics Division, NASA Langley Research Center, Senior member AIAA.x Aerospace Engineer, Vehicle Analysis Branch, Space Systems and Concepts Division, NASA Langley Research Center, Member AIAA.Copyright c 1998 by the American Institute of Aeronautics and Astronautics, Inc. No copyright is asserted in the United States under Title 17, U.S. Code. The U.S. Government has a r o y alty-free license to exercise all rights under the copyright claimed herein for governmental purposes. All other rights are reserved by the copyright o wner.two Mars Microprobes 1 are the second of the Deep Space missions from NASA's New Millennium Program O ce. Upon arrival at Mars, the penetrators will be released from the cruise stage and begin a free fall to the surface. This paper focuses on predicting the convective heating which the aeroshells will encounter during the hypersonic portion of that Mars entry. Knowledge of the...

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Influence of sonic-line location on Mars Pathfinder Probe aerothermodynamics

Cited by 76 publications

References 18 publications

Fluid Dynamics Analysis of a Space Vehicle Entering the Mars Atmosphere

Fluid Dynamics Analysis of a Space Vehicle Entering the Mars Atmosphere

Turbulent Supersonic/Hypersonic Heating Correlations for Open and Closed Cavities

Aerothermal heating predictions for Mars Microprobe

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