Abstract
In this paper a study of the secondary flow on an infinite yawed cylinder in a compressible stream is made at stagnation for unit Prandtl number and for a given Mach number. The secondary flow profiles are calculated for different edge inclination angles. The chordwise and spanwise velocity profiles given by Crabtree1 are used here in the calculation. It is found that the secondary flow profiles are the same for complementary edge inclination angles and they are maximum for the edge inclination angle of 45°. A comparison with the incompressible flow profiles2 is made. It is found that the magnitude of the secondary flow profiles in a compressible stream is less than that in an incompressible stream for the same edge inclination angle.
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References
Crabtree, L. F. .. “The compressible laminar boundary layer on a yawed infinite wing,”The Aer., Quarterly, July 1954,5.
Sinha, K. D. P. ..Dissertation Submitted for the Degree of Ph.D. in the University of Cambridge, 1956.
Schlichting, H. ..Boundary Layer Theory, Translated by Dr. J. Kestin, 1955.
Sowerby, L. .. “Secondary flow in a boundary layer,”R.A.E. Report No. Aero. 2512, 1954, A.R.C. 16832.
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Communicated by Dr. N. S. Nagendra Nath,f.a.sc.
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Sharma, R. Investigation of secondary flow on an infinite yawed cylinder in a compressible stream. Proc. Indian Acad. Sci. 59, 153–158 (1964). https://doi.org/10.1007/BF03049200
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DOI: https://doi.org/10.1007/BF03049200