Evaluation of active cooling systems for a Mach 6 hypersonic transport airframe /
by R.G. Helenbrook, W.A. Mcconarty, and F.M. Anthony.
Description
- Language(s)
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English
- Published
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Washington, D.C. : National Aeronautics and Space Administration ; 1971.
- Summary
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Transpiration and convective cooling concepts are examined for the fuselage and tail surface of a Mach 6 hypersonic transport aircraft. Hydrogen, helium, and water are considered as coolants. Heat shields and radiation barriers are examined to reduce heat flow to the cooled structures. The weight and insulation requirements for the cryogenic fuel tanks are examined so that realistic totals can be estimated for the complete fuselage and tail. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy construction materials. The results of the study are combined with results obtained on the wing structure, obtained in a previous study, to estimate weights for the complete airframe. The concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight.
- Note
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"NASA CR-1917."
"December 1971."
Cover title.
Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 04/05/06: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19720014374%5f1972014374.pdf.
- Physical Description
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v, 190 p. :
ill. ;
27 cm.
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University of Illinois at Urbana-Champaign
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