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Curvature of Shock Fronts in Shock Tubes
1.(a) R. A. Hartunian, Phys. Fluids 4, 1059 (1961);
1.(b) R. A. Hartunian, Master’s Thesis, Cornell University (1954).
2.J. Daen and P. C. T. De Boer, J. Chem. Phys. 36, 1222 (1962).
3.M. Sichel, Phys. Fluids 5, 1168 (1962).
4.S. C. Lin and W. I. Fyfe, Phys. Fluids 4, 238 (1961).
5.R. E. Duff and J. L. Young, Phys. Fluids 4, 812 (1961).
6.General Theory of High Speed Aerodynamics, edited by W. R. Sears (Princeton University Press, Princeton, New Jersey, 1954).
7.P. C. T. De Boer, Ph.D. Thesis, University of Maryland (1962).
8.E. Jahnke and F. Emde, Tables of Functions (Dover Publications Inc., New York, 1945), 4th Ed.
9.(a) H. Mirels, NACA TN 3401 (1955);
9.(b) H. Mirels, NACA TN 3712 (1956).
10.The experimental values reported in reference 5 were obtained by drawing a curve of the shock profile through points determined experimentally with circular detectors at 0.5, 0.75, 0.89, and 0.95. The curve did not go through the center of the detectors at and 0.89, and this could be qualitatively explained from the way in which the detectors respond to a symmetric pressure pulse incident at an angle. The present extension of the theory provides a check on the correctness of the shock profile. For example, it is possible to calculate the ratio of the axial displacement at and 0.89, respectively. Using (22) and (23), it is found that Figure 3 of reference 5 gives for this ratio 1.38, which is in very good agreement.
11.R. E. Duff, Phys. Fluids 2, 207 (1959).
12.A. Roshko, Phys. Fluids 3, 835 (1960).
13.W. J. Hooker, Phys. Fluids 4, 1451 (1961).
14.I. I. Glass and J. G. Hall, “Shock Tubes,” Section 18 of Handbook of Supersonic Aerodynamics (U.S. Government Printing Office, Washington, D.C., 1959).
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