Actions for Continued Development of a Global Heat Transfer Measurement System at AEDC Hypervelocity Wind Tunnel 9.

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Continued Development of a Global Heat Transfer Measurement System at AEDC Hypervelocity Wind Tunnel 9.

Author
Kurits, Inna
Published
[2007].
Physical Description
1 electronic document
Additional Creators
Hamner, M. P., Lewis, M. J., and Norris, Joseph D.
Online Version

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Summary
Heat transfer rates are an extremely important consideration in the design of hypersonic vehicles such as atmospheric reentry vehicles. This paper describes the development of a data reduction methodology to evaluate global heat transfer rates using surface temperature-time histories measured with the temperature sensitive paint (TSP) system at AEDC Hypervelocity Wind Tunnel 9. As a part of this development effort, a scale model of the NASA Crew Exploration Vehicle (CEV) was painted with TSP and multiple sequences of high resolution images were acquired during a five run test program. Heat transfer calculation from TSP data in Tunnel 9 is challenging due to relatively long run times, high Reynolds number environment and the desire to utilize typical stainless steel wind tunnel models used for force and moment testing. An approach to reduce TSP data into convective heat flux was developed, taking into consideration the conditions listed above. Surface temperatures from high quality quantitative global temperature maps acquired with the TSP system were then used as an input into the algorithm. Preliminary comparison of the heat flux calculated using the TSP surface temperature data with the value calculated using the standard thermocouple data is reported.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20070022279.
22nd International Congress on Instrumentation in Aerospace Simulation Facilities; 10-14 Jun. 2007; Pacific Grove, CA; United States.
Terms of Use and Reproduction
Copyright, Distribution as joint owner in the copyright.
View MARC record | catkey: 16001856