Heat Shield Cavity Parametric Experimental Aeroheating for a Mars Smart Lander

Liechty, Derek S.; Hollis, Brian R.

doi:10.2514/6.2002-2746

Cited by 12 publications

(13 citation statements)

References 4 publications

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“…During the mission concept-development phase, the entry vehicle was to be bolted to the cruise stage through the forebody heat shield. Testing of various cavity diameters and locations in the NASA Langley 20-inch Mach 6 Air Tunnel [110][111] showed that these penetrations would produce turbulent wedges on the forebody at Reynolds numbers well below those of natural smooth-body transition. Figure 17 is a sample thermal phosphor image from this test series.…”

Section: A Ground Test Resultsmentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The current status of aerothermal analysis for Mars entry missions is reviewed. The aeroheating environment of all Mars missions to date has been dominated by convective heating. Two primary uncertainties in our ability to predict forebody convective heating are turbulence on a blunt lifting cone and surface catalysis in a predominantly CO2 environment. Future missions, particularly crewed vehicles, will encounter additional heating from shock-layer radiation due to a combination of larger size and faster entry velocity. Localized heating due to penetrations or other singularities on the aeroshell must also be taken into account. The physical models employed to predict these phenomena are reviewed, and key uncertainties or deficiencies inherent in these models are explored.

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Section: A Ground Test Resultsmentioning

confidence: 99%

A Review of Aerothermal Modeling for Mars Entry Missions

Wright

Tang

Edquist

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…A previous MSL configuration (also a 70 deg sphere cone) was tested in the Langley Research Center Mach 6 air tunnel with an emphasis on heating augmentation due to possible forebody heat shield penetrations [3]. The results showed that turbulent heating levels downstream of isolated roughness elements on the lee side of the vehicle were large, and in fact exceeded even the smooth-wall computational predictions [4].…”

mentioning

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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“…As discussed in Ref. 3, the estimated experimental uncertainty of the heating data is approximately ±13%.…”

Section: Experimental Methodsmentioning

confidence: 90%

“…The computations and correlations are presented in this paper, while the wind tunnel data are presented in the companion paper by Liechty in Ref. 3. Comparisons of both laminar and turbulent aero heating predictions with the experimental data are also presented, as are predictions for the peak heating condition during Mars entry.…”

Section: Introductionmentioning

confidence: 99%

Boundary Layer Transition Correlations and Aeroheating Predictions for Mars Smart Lander

Hollis

Liechty

2002

32nd AIAA Fluid Dynamics Conference and Exhibit

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Laminar and turbulent perfect-gas air, Navier-Stokes computations have been performed for a proposed Mars Smart Lander entry vehicle at Mach 6 over a free stream Reynolds number range of 6.9xl0 6 /m to 2.4xl07/m (2.lxl0 6 /ft to 7.3xl0 6 /ft) for angles-of-attack ofO-deg, ll-deg, 16-deg, and 20-deg, and comparisons were made to wind tunnel heating data obtained at the same conditions. Boundary layer edge properties were extracted from the solutions and used to correlate experimental data on the effects of heat-shield penetrations (bolt-holes where the entry vehicle would be attached to the propulsion module during transit to Mars) on boundary-layer transition. A non-equilibrium Martian-atmosphere computation was performed for the peak heating point on the entry trajectory in order to determine if the penetrations would produce boundary-layer transition by using this correlation. (kg/m J )

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Heat Shield Cavity Parametric Experimental Aeroheating for a Mars Smart Lander

Cited by 12 publications

References 4 publications

A Review of Aerothermal Modeling for Mars Entry Missions

A Review of Aerothermal Modeling for Mars Entry Missions

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

Boundary Layer Transition Correlations and Aeroheating Predictions for Mars Smart Lander

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