Application of axisymmetric analog for calculating heating in three-dimensional flows

Hamilton, H. H.; Weilmuenster, K. J.; Dejarnette, Fred R.

doi:10.2514/3.25916

Cited by 41 publications

(11 citation statements)

References 10 publications

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“…Inviscid surface streamlines may b e calculated from the surface pressure distribution 5 or from the velocity components. 8 The approximate inviscid method 14;15 used here predicts accurate surface pressures, but the direction of the velocity on the surface is not accurate. Therefore, in the present method, streamlines are calculated from the surface pressures.…”

Section: Inviscid Surface Streamlinesmentioning

confidence: 99%

“…However, due to the excessive computer storage requirements and run times of these detailed approaches, they are impractical for the preliminary design environment where a range of geometries and ow parameters are to be studied. On the other hand, engineering inviscid-viscous methods 5,8 have been demonstrated to adequately predict the heating over a wide range of geometries and aerothermal environments. Various approximations in the inviscid and boundary-layer regions reduce the computer time needed to generate a solution.…”

Section: Introductionmentioning

confidence: 99%

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Engineering aerodynamic heating method for hypersonic flow

Christopher

Fred

1992

Journal of Spacecraft and Rockets

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A capability to calculate surface heating rates has been incorporated in an approximate three-dimensional inviscid technique. Surface streamlines are calculated from the inviscid solution, and the axisymmetric analog is then used along with a set of approximate convectiveheating equations to compute the surface heat transfer. The method is applied to blunted axisymmetric and three-dimensional ellipsoidal cones at angle of attack for the laminar ow of a perfect gas. The method is also applicable to turbulent and equilibrium-air conditions. The present technique predicts surface heating rates that compare favorably with experimental ground-test and ight data and numerical solutions of the Navier-Stokes NS and viscous shock-layer VSL equations.

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Section: Inviscid Surface Streamlinesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Engineering aerodynamic heating method for hypersonic flow

Christopher

Fred

1992

Journal of Spacecraft and Rockets

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“…This method has been in use since 1961 when it was developed by Cooke. 2 It has also been applied to Space-Shuttle-like geometries and repeatedly shown a good agreement with the experimental data, [3][4][5][6] with relatively small computational efforts compared to viscous CFD. The translation to 3D takes form in terms of a so-called metric coefficient, expressing the local spreading of the streamlines, determination methods for which have been proposed by Hamilton 7 and Parzhikar.…”

Section: Introductionmentioning

confidence: 81%

Re-entry Shape Optimisation Using the Axisymmetric Analogue Method with Modified Newtonian Technique Resolved Inviscid Flowfield

Brchnelova

Mooij

2021

AIAA Scitech 2021 Forum

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Re-entry shape and trajectory optimisation studies typically require hundreds to thousands of flow solutions to resolve the heat transfer and skin friction. Due to the fact that full CFD simulations and even Euler simulations are typically very expensive, this work presents a development of a much simpler technique, in which the modified Newtonian approximation is coupled with the axisymmetric-analogue-based viscous method. Afterwards, the developed technique is applied to the shape optimisation study of the DART module originally conducted by Sudmeijer and Mooij in 2002. Large differences in heat fluxes are observed mainly owing to the fact that the present method estimates the transition region from approximate transition criteria while the original study assumes the transition point to be fixed at the interface between the cone and the flare. This emphasises the sensitivity of design optimisation studies on delicate parameters such as the location of transition, which typically cannot be accurately predicted during the conceptual phase. Finally, the limitations of the current method are identified and the areas in which the technique will be improved further are outlined.

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“…Although this weak coupling improves surface pressure and heating results, it would be very difficult to apply it when inviscid solution is obtained using numerical solution of Euler equations. Because of these difficulties, all of the Euler/boundarylayer methods have simulated hypersonic flows with high Reynolds numbers, where displacement effect is negligible [13][14][15][16][17].…”

Section: Introductionmentioning

confidence: 99%

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

Parhizkar

Karimian

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A simple approach is proposed to incorporate the effect of viscous interaction in the calculation of aerodynamic heating of three-dimensional geometries by Euler/boundary-layer methods. In the present study, aerodynamic heating is calculated from the solution of a set of approximate convective-heating equations along the streamlines. These heating equations are derived using axisymmetric analogue. To determine streamline paths and flow properties along them, Euler equations are solved around the three-dimensional body. The effect of viscous interaction on the aerodynamic heating can be significant, especially if the Reynolds number is low. To incorporate this effect, the whole process should be repeated having considered the boundarylayer thickness all around the body. However, this approach causes different difficulties, and is not cost efficient as well. In the present work, the effect of boundary-layer thickness on the aerodynamic heating is incorporated through the correction of pressure distribution on the surface of the body. This approach of correcting pressure distribution is applied to spherical and elliptical blunted cones in laminar hypersonic flows. It is shown that the heating rates are improved in low Reynolds numbers, where viscous-interaction effect is significant. The present approach can result in a reduction of computational cost, when viscous interaction is significant in calculation of aerodynamic heating.

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Application of axisymmetric analog for calculating heating in three-dimensional flows

Cited by 41 publications

References 10 publications

Engineering aerodynamic heating method for hypersonic flow

Engineering aerodynamic heating method for hypersonic flow

Re-entry Shape Optimisation Using the Axisymmetric Analogue Method with Modified Newtonian Technique Resolved Inviscid Flowfield

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

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