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Out-of-plane force on a circular cylinder at large angles of inclination to a uniform stream

Published online by Cambridge University Press:  04 July 2016

P. J. Lamont  and
B. L. Hunt
P. J. Lamont
Affiliation:
Department of Aeronautical Engineering, University of Bristol
B. L. Hunt
Affiliation:
Department of Aeronautical Engineering, University of Bristol
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Extract

The force on a circular cylinder inclined to a uniform flow may be resolved into three components, one perpendicular to the plane defined by the axis of the cylinder and the upstream velocity vector (described in this report as the out-of-plane force) one within this plane and perpendicular to the axis (the in-plane normal force) and one within this plane and along the axis (the in-plane axial force).

It has become common practice, since Allen and Perkins, to model the flow over a circular cylinder inclined to a uniform flow by resolving the incident flow into two perpendicular component flows. One flow is taken to be parallel to the axis of the cylinder (axial flow) and the other normal to it (cross flow). The cross flow is not taken to be uniform over the whole length of the circular cylinder. Instead it is considered to be started impulsively at the nose and to develop over the length of the body in the same way that the impulsively-started flow over a cylinder develops with time.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 77 , Issue 745 , January 1973 , pp. 41 - 45
Copyright
Copyright © Royal Aeronautical Society 1973 

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References

1. Allen, H. J. and Perkins, E. W. A study of effects of viscosity on flow over slender inclined bodies of revolution. NACA Report 1048, 1951.Google Scholar
2. Schwabe, M. Pressure distribution in non-uniform two-dimensional flow. NACA TM 1039, 1943.Google Scholar
3. Sarpkaya, T. Separated flow about lifting bodies and impulsive flow about cylinders. AIAA Journal 4, pp 414–420, 1966.Google Scholar
4. Thomson, K. D. and Morrison, D. F. On the asymmetric shedding of vortices from slender cylindrical bodies at large angles of yaw. Weapons Research Establishment, Salisbury, South Australia. Technical Note HSA 106, 1965.Google Scholar
5. Thomson, K. D. and Morrison, D. F. The spacing position and strength of vortices in the wake of slender cylindrical bodies at large incidence. Weapons Research Establishment, Salisbury, South Australia. Report HSA 25, 1969.Google Scholar
6. McGregor, D. M. An experimental investigation of the oscillating pressures on a circular cylinder in a fluid stream. University of Toronto, UTIA TN 14, 1957.Google Scholar
7. Keefe, R. T. An investigation of the fluctuating forces acting on a stationary circular cylinder in a subsonic stream and of the associated sound field. University of Toronto, Report UTIA No 76, 1961.Google Scholar
8. Bishop, R. E. D. and Hassan, A. Y. The lift and drag forces on a circular cylinder in a flowing fluid. Proc Royal Soc of London, Vol 277, pp 32–50, 1964.Google Scholar
9. Drescher, H. Messung der auf querangestromte zylinder ausgeiibten zeitlich veranderten driicke. Z. f. Flugwiss 4. Heft 1/2, pp 17–21, 1956.Google Scholar
10. Gerrard, J. H. An experimental investigation of the oscillating lift and drag of a circular cylinder shedding turbulent vortices. J. Fluid Mech Vol 11, part 2, pp 244–256, 1961.Google Scholar
11. Schmidt, L. V. Measurement of fluctuating air loads on a circular cylinder. J. Aircraft, Vol 2, No 1, pp 49–55, 1965.Google Scholar
12. Mair, W. A. and Bostock, B. R. Private communication.Google Scholar