Effect Of Nose Cavity On Heat Transfer Rates To The Surface Of An Aeroshell Descending Through The Martian Atmosphere
- Paper number
IAC-12,A3,3A,13.p1,x12885
- Author
Mr. Sourabh Bhat, University of Petroleum and Energy Studies, India
- Coauthor
Mr. Rajesh Yadav, University of Petroleum and Energy Studies, India
- Coauthor
Dr. Ugur Guven, United States
- Coauthor
Mr. Karthik Sundarraj, University of Petroleum and Energy Studies, India
- Coauthor
Mr. Linsu Sebastian, University of Petroleum and Energy Studies, India
- Coauthor
Mr. Gurunadh Velidi, University of Petroleum and Energy Studies, India
- Coauthor
Mr. Seetesh Pande, Individual colaboration, India
- Year
2012
- Abstract
One of the more important problems in space exploration of Mars is the reentry of the vehicle into the Martian atmosphere. A successful reentry of a hypersonic speed spacecraft will require analytical simulations beforehand for a landing vehicle. A typical Aeroshell for Martian entry with forward facing axisymmetric cavity is investigated numerically for its drag and peak heat transfer rates using commercially available Computational Fluid Dynamics code Ansys Fluent 13.0. The cavities investigated are of circular and hyperbolic in shapes with rounded lips while the lip radius is varied from 10 cm to 100 cm. The Martian entry vehicle chosen for the simulation is 70-deg sphere cone Aeroshell with a diameter of 2.65m. The flow conditions simulated in the investigation are that of ballistic descent through the Martian atmosphere at an altitude of 44.2 km and Mach number of 22. A two dimensional axisymmetric computational fluid dynamic analysis is done for both perfect gas and non equilibrium chemically reacting gas assumptions with non catalytic wall. The Martian atmosphere for this simulation is assumed to be a homogenous mixture of 96% carbon dioxide, 2.5% Nitrogen and 1.5 % Argon. The presence of large cavity at the nose is likely to increase the drag coefficient thus increasing the ballistic coefficient which is helpful in slowing down the descent of the vehicle through the thin atmosphere. Also the presence of forward facing cavity reduces maximum heating rates at the stagnation region which is extremely desirable for safe delivery of payloads. This paper will investigate landing reentry under these conditions and it will derive necessary guidelines for such a prospect.
- Abstract document
- Manuscript document
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