CFD code comparisons for Mars entry simulations

Papadopoulos, Periklis; Prabhu, Dinesh K.; Olynick, David R.; Chen, Y.; Cheatwood, F. McNeil

doi:10.2514/6.1998-272

Cited by 21 publications

(12 citation statements)

References 17 publications

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“…The simplest model is to assume a noncatalytic surface. At the other extreme is the "supercatalytic" wall model, [29] in which the composition at the wall is forced to its lowest chemical enthalpy state (in this case pure CO 2 ). This model is not physically based in that finite-rate surface reactions are not modeled, but it serves as a useful limiting case because it is conservative: essentially all of the chemical enthalpy in the boundary layer is recovered at the wall.…”

Section: Numerical Methodologymentioning

confidence: 99%

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Wright

Olejniczak

Brown

et al. 2006

Journal of Thermophysics and Heat Transfer

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A series of shots are run in the T5 shock tunnel at California Institute of Technology to measure heating levels on a 70 blunt cone at angle of attack in an environment representative of the Mars Science Laboratory entry. Twenty shots are obtained in CO 2 over a range of enthalpies and pressures chosen to span the laminar and turbulent flow regimes. The data indicate that the lee side turbulent heating augmentation predicted by flight simulations is valid and must be accounted for during the design of the thermal protection system. Computational fluid dynamic simulations are generally in good agreement with the laminar data when employing a supercatalytic wall model, whereas turbulent simulations are in reasonable agreement when a noncatalytic wall model is used. The reasons for this discrepancy are unknown at this time. The turbulent heating augmentation is shown to be inversely related to freestream enthalpy. Changes in angle of attack between 11 and 16 are shown to have minimal impact on measured and computed heating. A transition criterion based on momentum thickness Reynolds number, analogous to that used in flight predictions, predicts onset with reasonable accuracy, although transition is observed to occur later than the current design criterion indicates.

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Section: Numerical Methodologymentioning

confidence: 99%

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Wright

Olejniczak

Brown

et al. 2006

Journal of Thermophysics and Heat Transfer

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“…DPLR has emerged as one of NASA's workhorse flow solvers for aerothermal calculations, and it has been extensively validated with flight and tunnel data. [14][15][16][17][18][19] DPLR is a structured, finite-volume code that solves the reacting Navier-Stokes equations and models finite-rate chemistry and thermal nonequilibrium. Inviscid fluxes were computed using a modified Steger-Warming flux splitting 20 that achieves third-order accuracy using MUSCL extrapolation (monotone upstream-centered scheme for conservation laws) with a minmod flux limiter.…”

Section: Environment Prediction Methodologymentioning

confidence: 99%

Radiation Modeling for the Reentry of the Hayabusa Sample Return Capsule

Winter

McDaniel

Chen

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Predicted shock-layer emission signatures of the Japanese Hayabusa capsule during its reentry are presented for comparison with flight measurements made during an airborne observation mission using NASA's DC-8 Airborne Laboratory. For each altitude, lines of sight were extracted from flow field solutions computed using an inhouse high-fidelity CFD code, DPLR, at 11 points along the flight trajectory of the capsule. These lines of sight were used as inputs for the line-by-line radiation code NEQAIR, and emission spectra of the air plasma were computed in the wavelength range from 300 nm to 1600 nm, a range which covers all of the different experiments onboard the DC-8. In addition, the computed flow field solutions were post-processed with the material thermal response code FIAT, and the resulting surface temperatures of the heat shield were used to generate thermal emission spectra based on Planck radiation. Both spectra were summed and integrated over the flow field. The resulting emission at each trajectory point was propagated to the DC-8 position and transformed into incident irradiance. Comparisons with experimental data are shown.

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“…LAURA has been used extensively to predict the aerodynamics and aerothermodynamics for Mars entry vehicles [2][3][4][19][20][21][22] . Perfect gas air conditions were used for the wind tunnel conditions and a finite-rate chemistry model was used for the flight conditions.…”

Section: Methodsmentioning

confidence: 99%

Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

Edquist

2006

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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CFD code comparisons for Mars entry simulations

Cited by 21 publications

References 17 publications

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Radiation Modeling for the Reentry of the Hayabusa Sample Return Capsule

Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

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