Investigation of hypersonic turbulent flow over the X-38 Crew Return Vehicle

Weber, Christian; Behr, R.; Weiland, Claus

doi:10.2514/6.2000-2601

Cited by 15 publications

(5 citation statements)

References 10 publications

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“…The peak heating rate at the reattachment point is overestimated by all models as is seen in Table 1. G-F-inp and Chien-inp show an enormous excess in heat transfer, a behavior that has also been shown by Weber et al [13] for various K-ε models. G-F-cmp and Chien-cmp show a lower excess in heat transfer compared with G-F-inp and Chien-inp, and the present model shows a smallest excess in heat transfer, as demonstrated in Table 1.…”

Section: -Degree Compression Ramp Test Casesupporting

confidence: 77%

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Development of A Two-Equation Turbulence Model for Hypersonic Shock Wave and Turbulent Boundary Layer Interaction

Liu

Lee

2011

AMM

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For hypersonic compressible turbulence, the correlations with respect to the density fluctuation must not be neglected. A Reynolds averaged K-ε model is proposed in the present paper to include these correlations, together with the Reynolds averaged Navier-Stokes equations to describe the mean flowfield. The K-equation is obtained from Reynolds averaged single-point second moment equations which are deduced from the instantaneous compressible Navier-Stokes equations. Under certain hypotheses and scales estimation of the compressible terms, the K-equation is simplified. The correlation terms of the fluctuation field appearing in the resulting K-equation, together with a conventional form of the ε-equation, are thus correlated with the variables in the average field. The new modeling coefficients of closure terms are optimized by computing the hypersonic turbulent flat-plate measured by Coleman and Stollery [J. Fliud Mech., Vol. 56 (1972), p. 741]. The proposed model is then applied to simulate hypersonic turbulent flows over a wedge compression corner angle of 34 degree. The predicting results compare favorably with the experimental results. Also, comparisons are made with other turbulence models. Additionally, an entropy modification function of Harten-Yee’s TVD scheme is introduced to reduce artificial diffusion near boundary layers and provide the required artificial diffusion to capture the shockwaves simultaneously.

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Section: -Degree Compression Ramp Test Casesupporting

confidence: 77%

“…Velocity profiles in wall units are shown in Figure 1c. The logarithmic law of the wall u + =1/кln(y + )+C is also shown with к=0.35 and C=5.0 [13]. All models yield a von Karman constant that is slightly smaller than that from the one suggested by So et al [14].…”

Section: Flat Plate Test Casementioning

confidence: 59%

Development of A Two-Equation Turbulence Model for Hypersonic Shock Wave and Turbulent Boundary Layer Interaction

Liu

Lee

2011

AMM

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show abstract

“…The models were investigated in super-and hypersonic flat plate boundary layers, on a compression ramp at M ∞ = 9.22 and on a hypersonic flow over the X-38 vehicle at M ∞ = 6, where windtunnel data are available from NASA Langley Research Center. The complete issue of the numerical simulations using ASTRIUM's DAVIS-VOL code are reported in [19]. Here a selection of these results will be given.…”

Section: Advanced Turbulence Modellingmentioning

confidence: 98%

Aerothermodynamics for reusable launch systems

Weiland¹,

Longo²,

Gülhan³

et al. 2004

Aerospace Science and Technology

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“…(The two-layer method was not used to predict flap heating.) Experimentally, the boundary layer was forced turbulent via discrete roughness and the resulting heating distribution compared to turbulent prediction 53,58,59 (Fig. 26b).…”

Section: Windward Flap Heatingmentioning

confidence: 99%