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SIMULATIONS OF HYPERSONIC FLOW PAST A RE-ENTRY CAPSULE USING DSMC METHOD

R.V. Reji, S. Anil Lal

Fluid Dynamics Lab, Department of Mechanical Engineering, College of Engineering Trivandrum, Kerala, India

* Corresponding Author: Email: email

Frontiers in Heat and Mass Transfer 2016, 7, 1-8. https://doi.org/10.5098/hmt.7.27

Abstract

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. 0 o , 20o&40o . 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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Cite This Article

Reji, R., Lal, S. A. (2016). SIMULATIONS OF HYPERSONIC FLOW PAST A RE-ENTRY CAPSULE USING DSMC METHOD. Frontiers in Heat and Mass Transfer, 7(1), 1–8.



cc This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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