Hostname: page-component-7bb8b95d7b-2h6rp Total loading time: 0 Render date: 2024-10-05T22:16:59.974Z Has data issue: false hasContentIssue false
  • English
  • Français

The supersonic and low-speed flows past circular cylinders of finite length supported at one end

Published online by Cambridge University Press:  28 March 2006

D. M. Sykes
D. M. Sykes
Affiliation:
Department of the Mechanics of Fluids, University of Manchester
At present at The War Office, Armament Research and Development Establishment, Fort Halstead.
Get access Rights & Permissions [Opens in a new window]

Abstract

The flow past circular cylinders of finite length, supported at one end and lying with their axes perpendicular to a uniform stream, has been investigated in a supersonic stream at Mach number 1.96 and also in a low-speed stream. In both stream it was found that the flow past the cylinders could be divided into three regions: (a) a central region, (b) that near the free end of the cylinder, and (c) that near the supported end. The locations of the second and third regions were found to be almost independent of the cylinder length-to-diameter ratio, provided that this exceeded 4, while the flow within and the extent of the first region were dependent on this ratio. Form-drag coefficients determined in the central region in the supersonic flow were in close agreement with the values determined at the same Mach number by other workers. In the low-speed flow the local form-drag coefficients were dependent on length-to-diameter ratio and were always less than that of an infinite-length cylinder at the same Reynolds number.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 12 , Issue 3 , March 1962 , pp. 367 - 387
Copyright
© 1962 Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Goldstein, S. 1938 (Ed.) Modern Developments in Fluid Dynamics, Vol. II. Oxford: Clarendon Press.
Gowen, F. E. & Perkins, E. W. 1953 N.A.C.A. T.N. 2960.
Gregory, N. & Walker, W. S. 1950 Aero. Res. Coun., Lond., Rep. no. 13436 (FM 1482).
Kim, C. S. 1956 J. Phys. Soc. Jap. 11, 439–45.
Kondo, J. 1957 Proc. 7th Jap. Nat. Cong. App. Mech. 167–72.
Livesey, J. L. 1956 J. Aero. Sci. 23, 949–55.
McKinney, L. W. 1960 N.A.S.A. T.N. D-540.
Pankhurst, R. C. & Holder, D. W. 1952 Wind Tunnel Technique. London: Pitman.
Polhamus, E. C. 1959 N.A.S.A. T.R. R-29.
Sharp, A. W. 1959 J. Fluid Mech. 5, 445–69.
Thom, A. 1929 Aero Res. Coun., Lond., R. & M. 1194.
Uchida, S. & Yasuhara, M. 1956 J. Aero. Sci. 23, 830–45.
Wieselsberger, C. 1923 Ergb. Aerod. Versuchsanstalt zu Göttingen, 2, 23–8.
Winternitz, F. A. L. 1955 Engineer, 199, 729–32.