IN very high performance aircraft—that is aircraft flying at high speeds and high altitudes—the thermal problems confronting the mechanical engineer are becoming progressively more and more severe. Atmospheric Temperature ranges of upwards of 100 deg. C combined with thermodynamic effects due to the high speeds, widely varying air pressure and moisture content are encountered and very rigid temperature limits for the various component parts of the aircraft have to be met with equipment of a minimum size and weight and without materially affecting the overall performance of the machine.
Rendel, D. (1954), "Thermal Problems of High Performance Flight: A Further Contribution to the Bristol Conference on Thermal Stress Organized by the Stress Analysis Group of the Institute of Physics", Aircraft Engineering and Aerospace Technology, Vol. 26 No. 7, pp. 220-223. https://doi.org/10.1108/eb032443Download as .RIS
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