Comparisons Between DSMC and Navier-Stokes Solutions and Measurements in Regions of Laiviinar Shock Wave Boundary Layer Interaction in Hypersonic Flows

Holden, Michael; Wadhams, Timothy; Harvey, J. K.; Candler, Graham V.

doi:10.2514/6.2002-435

Cited by 34 publications

(39 citation statements)

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“…Again the recovery of the pressure and heat transfer towards the simple attached flow laminar values at the downstream end of the second cone was convincing evidence that the flows were not transitional or turbulent even after the separation. Figure 2 shows the pressure and heat transfer coefficient results produced by Moss [3] using DSMC for the hollow cylinder/flare body for test case 9 (see Table I). In this flow the weak-interaction bow shock coalesces with the shock generated by the separation (which occurs at about x/L = 0.4) to form a strengthened shock wave.…”

Section: Configurations Testedmentioning

confidence: 99%

“…The tests were conducted at Mach numbers in the range of 9.5 to 12.5 and for unit Reynolds numbers going from 1.19E+05/m to 1.46E+06/m. Full details of the model geometries and revised test conditions are given in Holden et al [3] and in an extensive database called CUBDAT [4]. Both configurations are axisymmetric and so avoid the experimental uncertainties that occur due to the finite span of the wind tunnel models with supposedly "two-dimensional" tests on, for example, flat plates and wedges.…”

Section: Configurations Testedmentioning

confidence: 99%

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Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Harvey¹,

Holden²,

Candler³

2003

AIP Conference Proceedings

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Abstract. This paper discusses the recent progress with a validation exercise to examine the effectiveness of DSMC and NavierStokes in predicting complex flows involving shock/shock and shock/boundary layer interactions under laminar hypersonic conditions. The exercise is based on experiments conducted in the Aerothermal and Aero-Optics Evaluation Center shock tunnels using nitrogen. Under moderately rarefied conditions Navier-Stokes methods have performed very well in capturing the details of flow structure especially when non-equilibrium and slip effects are accounted for, whereas DSMC has not been as successful. In particular, the size of the separation regions is underestimated. This paper presents redefined test conditions accounting for vibrational non-equilibrium which have been substantiated by correlations obtained for pressure and heat transfer on the hollow cylinder and cone forebodies. Details are announced of two new lower density test conditions for future validation studies.

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Section: Configurations Testedmentioning

confidence: 99%

Section: Configurations Testedmentioning

confidence: 99%

Validation of DSMC/Navier-Stokes Computations for Laminar Shock Wave/Boundary Layer Interactions in Hypersonic Flow

Harvey¹,

Holden²,

Candler³

2003

AIP Conference Proceedings

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“…A recent study of the flow in the LENS wind tunnel [7] shows that the flow is vibrational non-equilibrium and free-stream parameters have to be corrected. New parameters for Run 11 case is called here as Run 11c.…”

Section: Flow Conditions and Numerical Methodsmentioning

confidence: 99%

“…An additional investigation [7] of flow properties in the LENS wind tunnel revealed that the flow is vibrationally non-equilibrium under the conditions considered. As a result, the translational temperature and the velocity in the LENS test section are lower than the values reported previously.…”

Section: Run 11c Casementioning

confidence: 99%

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Statistical Simulation of Near-Continuum Flows with Separation

Markelov¹,

Ivanov²,

Gimelshein³

et al. 2003

AIP Conference Proceedings

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Abstract. Statistical simulation of flow around a hollow cylinder flare was performed for LENS Run 9 and Run 11 cases. A comparison with experimental and available numerical results shows that the kinetic approach predicts flow properties rather accurately if all the requirements inherent in the DSMC method (time step, cell size, and the total number of molecules) are satisfied. A recent study of the flow in the LENS wind tunnel shows that the flow is vibrationally non-equilibrium. A computation with corrected flow conditions for Run 11 case predicts lower heat fluxes over the forebody and the aft part of the flare which are in good agreement with experimental data.

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