Quasi-transonic flow past delta wings
Author:
Gilberto Schleiniger
Journal:
Quart. Appl. Math. 45 (1987), 265-277
DOI:
https://doi.org/10.1090/qam/99612
MathSciNet review:
QAM99612
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References |
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Abstract: Linearized supersonic theory for flows past delta wings must be corrected for the cases of wing sweepback angles close to the Mach angle. Results of calculations based on a local transonic expansion valid near the leading edge are presented.
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L. E. Fraenkel and R. Watson, The formulation of a uniform approximation for thin conical wings with sonic leading edges, Symposium Transsonicum (K. Oswatitsch, (ed.), Springer, Berlin, 1964
P. A. Lagerstrom, Linearized supersonic theory of conical wings, NACA TN 1685 (1950)
H. W. Liepmann and A. Roshko, Elements of gasdynamics, J. Wiley, New York, 1957
E. S. Love, Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles, NACA REPORT 1238 (1949)
E. M. Murman and J. D. Cole, Calculations of plane steady transonic flows, AIAA J. 9, 114–121 (1971)
E. M. Murman, Analysis of embedded shock waves calculated by relaxation methods, AIAA J. 12 (5), 626–633 (1974)
A. E. Puckett, Supersonic wave drag of thin airfoils, J. Aeronaut. Sci. 13 (9), 475–484 (1946).
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Article copyright:
© Copyright 1987
American Mathematical Society
