Base flow investigation of the Apollo AS-202 Command Module

Walpot, L.; Wright, Michael J.; Noeding, Peter; Schrijer, F.F.J.

doi:10.1016/j.paerosci.2011.06.006

Cited by 12 publications

(8 citation statements)

References 5 publications

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“…Zappa and Reinecke observed that the flow can remain attached for angles between the free flow and the wall up to 28° [11]. Depending on the geometry and the incoming flow conditions, the maximal heat flux resulting from this flow topology can reach 10 % of the stagnation heat flux [5,12]. Moreover, results from the CNES database have shown that for geometries such as cylinders, boxes or flat plates, a peak heat flux is visible on the lee side near the upwind edge.…”

Section: Wall Heat Flux and Pressure Coefficient In The Shadow Region Of Space Debrismentioning

confidence: 99%

Reduced order models for heat flux and pressure distributions on space debris afterbodies

et al. 2021

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The prediction of the on-ground risk caused by re-entering space debris requires accurate and computationally affordable models to compute wall heat flux and pressure coefficient C p at every stage of the reentry. Such models already exist for the wind area of the debris, i.e. the area directly impinged upon by fictitious lines parallel to the incoming flow. But the heat flux and C p are often neglected in the shadow area, even though they can be relatively high for certain shapes of debris. The present work focuses on developing reduced order models for heat flux and C p distributions in the shadow area of space debris, for hypersonic continuous flow conditions. We identified four phenomena which appear in the shadow area and cause relatively high levels of these aerodynamic quantities (attached flow, detached flow with fluid reattachment, detached flow with solid reattachment and shock-shock interactions). Models were developed for the heat flux and C p distributions caused by attached flows on the lee side of cylindrical geometries using the Proper Orthogonal Decomposition (POD) and interpolation method. Using this method, it is possible to reduce the number of required data by efficiently exploring the parameters domain of variation. The sample points were chosen thanks to an adaptive design of experiments, and the input data for the models were obtained by 3D Navier-Stokes computations of the flow around cylinders at incidence. The analysis of the computational results highlighted the influence of the Reynolds number based on the cylinder diameter Re D,∞ on the heat flux and pressure distributions. Reduced-order models were created for three input parameters (length L, diameter D and angle of attack α) and fixed incoming flow conditions, using the POD and interpolation method, and then were extended to other upstream hypersonic continuous flow conditions by more classical approaches based on non-dimensional quantities. Finally, the reentry trajectories of two different cylindrical debris were computed with and without the new models developed, to demonstrate their influence

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Section: Wall Heat Flux and Pressure Coefficient In The Shadow Region Of Space Debrismentioning

confidence: 99%

Reduced order models for heat flux and pressure distributions on space debris afterbodies

et al. 2021

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“…The contour integration of the inviscid flux vector is approximated at the side of the computational grid and the summation is carried out over the four edges of the grid. 12,13 Then, the viscous terms are defined at the center of each cell.…”

Section: Inviscid Viscous Fluxes and Artificial Dissipationmentioning

confidence: 99%

“…The separation shear layer eventually coalesces, forming the neck or narrowest point in the wake. 13 A wake shock is formed at that point, which compresses the flow leading to local maxima in pressure and temperature. Further away from the neck is far wake region, which extends for many body diameters downstream as the momentum deficit created by the passing module is slowly recovered.…”

Section: Solutions By 3d Navier-stokes Equationsmentioning

confidence: 99%

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Investigation of computational flow fields and aeroacoustic characteristics over a re-entry command module

Rose

Saranya

Benifa

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Design and analysis of a wind tunnel model for re-entry vehicle configuration is a prolonged and expensive mission. As the aerothermodynamics loads acting on the vehicle are based on geometry, various wind tunnel models need to be built for aerodynamic characterization by experimental procedure. Alternatively, the intention of this article is to present the influence of aerodynamic and aero acoustic characteristics of a typical re-entry capsule by computational fluid dynamics analysis. A typical re-entry capsule is designed using computational design software and it is imported to a computational fluid dynamics solver and flow simulations are done at various input conditions. Stanford University unstructured computational fluid dynamics solver is used for this purpose to solve complex, multiphysics analysis, and optimization tasks. Computational fluid dynamics results are presented to understand the influence of aerodynamic characteristics of a typical re-entry capsule, by visualizing the flow field around the command module at all the flow regimes like subsonic, supersonic, and hypersonic flows. The flow fields are studied in detail and regions of high flow unsteadiness due to wake separated flow zone are identified. Aeroacoustic loading on the command module at these regions especially at shock wave zone are predicted in the present investigation with high order of accuracy.

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“…Though a large number of simulations using DSMC method can be found in literature, the simulation of high speed flow over objects such as re-entry objects are found very few. Notable investigations on the re-entry simulations reported are flow over Apollo (Glass et al, 2006;Walpot et al, 2012), Orion (Votta et al, 2013;Palharini, 2014)] and OREX capsule (Moss et al, 1996). In India, the important mile stone towards re-entry capsule has been due to the Space Recovery Experiment (SRE).…”

Section: Introductionmentioning

confidence: 99%

Simulations of Hypersonic Flow Past a Re-Entry Capsule Using DSMC Method

Lal¹,

Reji²

2016

Frontiers in Heat and Mass Transfer

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DSMC simulation of re-entry of an object with shape and size close to that of ISRO's Space Recovery Experiment (SRE) capsule has been analysed using the open-source tool dsmcFoam for three altitude conditions, viz. 85 km, 100 km and 115 km, and for three angles of attack, viz.o . The hypersonic free stream velocity of 8000 m/s and boundary surface temperature of 300 K have been used for the simulations. The variation of parameters such as surface heat flux, surface pressure, shear stress, slip velocity, temperature jump and integrals such as total heat transfer, pressure drag and frictional drag are reported and discussed in this paper. The variation of temperature in the flow domain and along the stagnation line are able to clearly distinguish the shock structure and shock stand-off distance. The variation of local number density and the effects of such variations on the surface temperature and heat flux are discussed. A lower value for nose radius in SRE capsule is found to result in a higher value for peak heat flux compared to other re-entry capsules investigated.

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Base flow investigation of the Apollo AS-202 Command Module

Cited by 12 publications

References 5 publications

Reduced order models for heat flux and pressure distributions on space debris afterbodies

Reduced order models for heat flux and pressure distributions on space debris afterbodies

Investigation of computational flow fields and aeroacoustic characteristics over a re-entry command module

Simulations of Hypersonic Flow Past a Re-Entry Capsule Using DSMC Method

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