Assessment of Turbulent CFD against STS-128 Hypersonic Flight Data

Wood, William A.; Kleb, William L.; Hyatt, Andrew J.

doi:10.2514/6.2010-4889

Cited by 2 publications

(2 citation statements)

References 13 publications

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“…No additional equations are solved and thus it is computationally efficient while still introducing the first level of turbulent physics into the simulation. 15…”

Section: A Current Standard Practice -Block Zonal Grid With Baldwin-mentioning

confidence: 99%

Influence of Turbulence Modeling On Aftbody Surface Heating Prediction For A Hypersonic Entry Capsule

Neitzel

Boyd

2013

44th AIAA Thermophysics Conference

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A densely populated aerothermal database based on CFD is needed for the design of a hypersonic entry capsule. Traditionally, this has required the use of low fidelity turbulence models in order to make the computational effort for the large number of CFD runs more tractable. This compromise in accuracy is generally acceptable for the majority of the database. However, comparisons with experimental data have shown that the aftbody heating prediction accuracy is poor for high angle of attack cases. The presence of a large flow separation region appears to be the culprit due to the breakdown of the turbulence modeling assumptions in the region. The presented research investigates the importance of the turbulence modeling in the aftbody heating prediction for high angle of attack cases. The current practice of a simple RANS model is compared with the more sophisticated DES turbulence modeling. The models are investigated for accuracy (compared to experimental data) and for computational cost.

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“…No additional equations are solved and thus it is computationally efficient while still introducing the first level of turbulent physics into the simulation. 15…”

Section: A Current Standard Practice -Block Zonal Grid With Baldwin-mentioning

confidence: 99%

Influence of Turbulence Modeling On Aftbody Surface Heating Prediction For A Hypersonic Entry Capsule

Neitzel

Boyd

2013

44th AIAA Thermophysics Conference

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“…Figure 2 is another comparison of turbulent CFD predictions with a thermocouple temperature history, this time with STS-128 flight data. 9 Again there is a difference in trend between turbulent CFD and measurement for Mach numbers greater than 11.…”

Section: Introductionmentioning

confidence: 96%

Assessment of CFD Hypersonic Turbulent Heating Rates for Space Shuttle Orbiter

Wood

Oliver

2011

42nd AIAA Thermophysics Conference

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Turbulent CFD codes are assessed for the prediction of convective heat transfer rates at turbulent, hypersonic conditions. Algebraic turbulence models are used within the DPLR and LAURA CFD codes. The benchmark heat transfer rates are derived from thermocouple measurements of the Space Shuttle orbiter Discovery windward tiles during the STS-119 and STS-128 entries. The thermocouples were located underneath the reaction-cured glass coating on the thermal protection tiles. Boundary layer transition flight experiments conducted during both of those entries promoted turbulent flow at unusually high Mach numbers, with the present analysis considering Mach 10-15. Similar prior comparisons of CFD predictions directly to the flight temperature measurements were unsatisfactory, showing diverging trends between prediction and measurement for Mach numbers greater than 11. In the prior work, surface temperatures and convective heat transfer rates had been assumed to be in radiative equilibrium. The present work employs a one-dimensional time-accurate conduction analysis to relate measured temperatures to surface heat transfer rates, removing heat soak lag from the flight data, in order to better assess the predictive accuracy of the numerical models. The turbulent CFD shows good agreement for turbulent fuselage flow up to Mach 13. But on the wing in the wake of the boundary layer trip, the inclusion of tile conduction effects does not explain the prior observed discrepancy in trends between simulation and experiment; the flight heat transfer measurements are roughly constant over Mach 11-15, versus an increasing trend with Mach number from the CFD. Nomenclature

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Assessment of Turbulent CFD against STS-128 Hypersonic Flight Data

Cited by 2 publications

References 13 publications

Influence of Turbulence Modeling On Aftbody Surface Heating Prediction For A Hypersonic Entry Capsule

Influence of Turbulence Modeling On Aftbody Surface Heating Prediction For A Hypersonic Entry Capsule

Assessment of CFD Hypersonic Turbulent Heating Rates for Space Shuttle Orbiter

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