Radiative and total heat transfer measurements to a Titan Explorer model

Capra, Bianca R. & Morgan, Richard G. (2006) Radiative and total heat transfer measurements to a Titan Explorer model. In Proceedings of the 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, American Institute of Aeronautics and Astronautics, Canberra, Australia, pp. 1-4.

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Radiative and total heat transfer at the flow stagnation point of a 1:40.8 binary scaled model of the Titan Explorer vehicle were measured in the X3 expansion tube. Results from the current study illustrated that with the addition of CH4 into a N2 test gas radiative heat transfer could be detected. For a test gas of 5% CH4 and 95% N2, simulating an atmospheric model for Titanic aerocapture, approximately 4% of the experimentally measured total stagnation point heat transfer was found to be due to radiation. This was in comparison to < 1% measured for a test gas of pure nitrogen. When scaled to the flight vehicle, experimental results indicate a 64% contribution of radiation (test gas 5% CH4/95% N2). Previous numerical results however have predicted this contribution to be between 80-92%. Thus, experimental results from the current study suggest that numerical analyses are over-predicting the radiative heat transfer on the flight vehicle.

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ID Code: 70322
Item Type: Conference Paper
Refereed: No
DOI: 10.2514/6.2006-7934
ISBN: 978-1-62410-050-5
Divisions: Current > QUT Faculties and Divisions > Science & Engineering Faculty
Copyright Owner: Copyright 2006 [please consult the authors]
Deposited On: 16 Dec 2014 00:11
Last Modified: 21 Jun 2017 00:02

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