Transition Onset and Turbulent Heating Measurements for the Mars Science Laboratory Entry Vehicle

Hollis, Brian R.; Liechty, Derek S.; Wright, Michael J.; Holden, Michael; Wadhams, Timothy; MacLean, Matthew; Dyakonov, Artem A.

doi:10.2514/6.2005-1437

Cited by 51 publications

(72 citation statements)

References 14 publications

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“…This is in contrast to the laminar shots, where the noncatalytic solution is always significantly lower than the T5 data. The same result is observed for the other turbulent shots in this series, and also in the simulations of test data from the LENS facility [5]. The reasons for this discrepancy are not clear at this time.…”

Section: B Three-dimensional Casessupporting

confidence: 62%

“…The same results hold for the other 0 deg cases as well. Similar trends are also observed in the tests performed in the LENS shock tunnel [5]. It is somewhat surprising that the supercatalytic model accurately predicts the heat transfer for these cases because, as stated in the preceding section, this model was developed mainly as a convenient means to determine an upper bound on the predicted heat flux.…”

Section: A Axisymmetric Casessupporting

confidence: 59%

“…17 shows that T5 data from shot 2264 (h 0 11:6 MJ=kg, p 0 58:9 MPa, 16 deg) seems to indicate somewhat higher heating levels on the wind centerline (near y 0:05 m) than the laminar predictions. This result is interesting when compared with the apparent wind side heating augmentation reported for similar tests by Olejniczak et al [6] and Hollis et al, [5] but there is insufficient evidence to reach any conclusions based on these data.…”

Section: F Wind Side Heating Augmentationcontrasting

confidence: 42%

“…Secondary objectives are to determine the ability of the current design turbulence models to predict turbulent heating levels and to gain some insight into the appropriate transition criteria to apply to this type of flowfield. Additional testing has also been conducted in the high enthalpy LENS shock tunnel at the Calspan University of Buffalo Research Center as well as the Langley Mach 6 wind tunnel; the results of these tests are presented in [5].…”

mentioning

confidence: 99%

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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: B Three-dimensional Casessupporting

confidence: 62%

Section: A Axisymmetric Casessupporting

confidence: 59%

Section: F Wind Side Heating Augmentationcontrasting

confidence: 42%

mentioning

confidence: 99%

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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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“…The complete set of equilibrium reservoir conditions as computed by the CREST code is given in Table 1. Prediction of Vibrational Relaxation of CO 2 …”

Section: A Nominal Conditions On the Modelmentioning

confidence: 99%

Numerical Assessment of Data in Catalytic and Transitional Flows for Martian Entry

MacLean

Holden²

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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The conditions for a typical run from the MSL phase two study of transition that was performed in the LENS facility have been analyzed to understand the sensitivity to the freestream conditions of the facility. A simplified analysis technique has been used based on energy accounting to freeze specified portions of the chemical or vibrational energy during the expansion process in the nozzle. The effect of freezing this energy results in increased shock standoff distance that better matches the measured shock shape. Based on several cases, it was found that freezing approximately 42% of the total enthalpy of the flow in the vibration mode results in the best agreement with the measured shock shape. This modified condition also results in significantly better agreement with the measured surface heat transfer at the stagnation point and with the measured pressure at the shoulders of the model. Based on this adjusted freestream condition, the surface heat transfer data shows behavior generally consistent with fully-catalytic recombination on the cold wall. This behavior is consistent with previous results obtained in shock tunnel facilities in carbon dioxide, air, and nitrogen. Although the mechanism causing this frozen energy in the flow has not been identified, the sensitivity of the transition onset point of the flowfield to this phenomenon has been estimated to be less than 10% based on a simple transition criterion.

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Local Stability Analysis of Laminar-Turbulent Boundary Layer Transition on Blunt Generic Re-Entry Capsules

Theiß

Lichtmes

Hein

2016

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Transition Onset and Turbulent Heating Measurements for the Mars Science Laboratory Entry Vehicle

Cited by 51 publications

References 14 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

Numerical Assessment of Data in Catalytic and Transitional Flows for Martian Entry

Local Stability Analysis of Laminar-Turbulent Boundary Layer Transition on Blunt Generic Re-Entry Capsules

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