Abstract
center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds/' NACA TR 1307 (1957). 9 Shanley, F. R., Weight-Strength Analysis of Aircraft Structures (Dover Publications Inc., New York, I960), 2nd ed. 10 Dickson, J. A., Thermal protection with a temperature capability to 2500°F, for cool structures,' Proceedings of Conference on Aerodynamically Heated Structures, edited by P. E. Glasser (Prentice-Hall, Englewood Cliffs, N. J., 1962), pp. HI134. 11 Fraiisiscus, L. C. and Lesberg, E. A., Effects of nozzle recombination on hypersonic ramjet performance: II. Analytical investigation, AIAA J. 1, 2077-2083 (1963). 12 Carlsoii, H. W., The lower bound of attainable sonic-boom overpressure and design methods of approaching this limit, NASA TN D-1494 (1962). 13 Hutchinson, H. A., Defining the sonic boom problem, Astronaut. Aerospace Eng. 1 (December 1963). 14 McLean, F. E., Some iionasymptotic effects on the sonic boom of large airplanes, NASA TN D-2877 (1965). 15 Bryson, A. E,, Denham, W. F., Caroll, F. J.,' and Mikami, K., Determination of lift or drag programs to minimize re-entry heating, J. Aerospace Sci. 29, 420-430 (1962). 16 Stancil, R. T., A new approach to steepest-ascent trajectory optimization, AIAA Preprint 63-223 (June 1963). 17 Specification for Engines, Aircraft, Turbojet. Model. Military Specification MIL-E-5008B (January 1959).
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