Expansion tube operating conditions for studying nonequilibrium radiation relevant to Titan Aerocapture

Brandis, A. M., Gollan, R. J., Scott, M. P., Morgan, R. G. and Jacobs, P. A. (2006). Expansion tube operating conditions for studying nonequilibrium radiation relevant to Titan Aerocapture. In: Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference. 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, California, USA, (2074-2083). 9-12 July 2006.

Author Brandis, A. M.
Gollan, R. J.
Scott, M. P.
Morgan, R. G.
Jacobs, P. A.
Title of paper Expansion tube operating conditions for studying nonequilibrium radiation relevant to Titan Aerocapture
Conference name 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Conference location California, USA
Conference dates 9-12 July 2006
Proceedings title Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Journal name Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Place of Publication USA
Publisher American Institute of Aeronautics and Astronautics
Publication Year 2006
Sub-type Fully published paper
ISBN 1563478188
9781563478185
Volume 3
Start page 2074
End page 2083
Total pages 10
Collection year 2006
Language eng
Abstract/Summary The predictions of nonequilibrium radiation in the shock layer for a Titan aerocapture aeroshell vary significantly amongst Computational Fluid Dynamics (CFD) analyses and are limited by the physical models of the nonequilibrium flow processes. Of particular interest are nonequilibrium processes associated with the CN molecule which is a strong radiator. It is necessary to have experimental data for these radiating shock layers which will allow for validation of the CFD models. This paper describes the development of a test flow condition for subscale aeroshell models in a superorbital expansion tunnel. We discuss the need for a Titan gas condition that closely simulates the atmospheric composition and present experimental data of the free stream test flow conditions. Furthermore, we present finite-rate CFD calculations of the facility to estimate the remaining free stream conditions, which cannot be directly measured during experiments.
Subjects EX
290299 Aerospace Engineering not elsewhere classified
690302 Space transport
Q-Index Code E1
Institutional Status UQ

 
Versions
Version Filter Type
Citation counts: Scopus Citation Count Cited 0 times in Scopus Article
Google Scholar Search Google Scholar
Created: Thu, 23 Aug 2007, 22:29:19 EST