Hostname: page-component-586b7cd67f-dlnhk Total loading time: 0 Render date: 2024-11-29T00:48:37.875Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental verification of an Oseen flow slender body theory

Published online by Cambridge University Press:  25 May 2010

E. CHADWICK ,
H. M. KHAN ,
M. MOATAMEDI ,
M. MAPPIN  and
M. PENNEY
E. CHADWICK*
Affiliation:
School of Computing, Science and Engineering, University of Salford, Salford M5 4WT, UK
H. M. KHAN
Affiliation:
School of Computing, Science and Engineering, University of Salford, Salford M5 4WT, UK
M. MOATAMEDI
Affiliation:
Narvik University College, Lodve Langes Gate 2, Narvik, N-8505Norway
M. MAPPIN
Affiliation:
School of Computing, Science and Engineering, University of Salford, Salford M5 4WT, UK
M. PENNEY
Affiliation:
School of Computing, Science and Engineering, University of Salford, Salford M5 4WT, UK
*
†Email address for correspondence: [email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

Consider uniform flow past four slender bodies with elliptical cross-section of constant ellipticity along the length of 0, 0.125, 0.25 and 0.375, respectively, for each body. Here, ellipticity is defined as the ratio of the semiminor axis of the ellipse to the semimajor axis. The bodies have a pointed nose which gradually increases in cross-section with a radius of curvature 419 mm to a mid-section which then remains constant up to a blunt end section with semimajor axis diameter 160 mm, the total length of all bodies being 800 mm. The bodies are side-mounted within a low-speed wind tunnel with an operational wind speed of the order 30 m s−1. The side force (or lift) is measured within an angle of attack range of −3° to 3° such that the body is rotated about the major axis of the ellipse cross-section. The lift slope is determined for each body, and how it varies with ellipticity. It is found that this variance follows a straight line which steadily increases with increasing ellipticity. It is shown that this result is predicted by a recently developed Oseen flow slender body theory, and cannot be predicted by either inviscid flow slender body theory or viscous crossflow theories based upon the Allen and Perkins method.

Type
Papers
Information
Journal of Fluid Mechanics , Volume 654 , 10 July 2010 , pp. 271 - 279
Copyright
Copyright © Cambridge University Press 2010

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.)

Footnotes

‡

H. M. Khan is also a permanent faculty member at College of Aeronautical Engineering, National University of Sciences and Technology (NUST), Pakistan

References

REFERENCES

Allen, H. J. & Perkins, E. W. 1951 A study of effects of viscosity on flow over slender inclined bodies of revolution. Tech. Rep. Report 1048. NACA.Google Scholar
Chadwick, E. 1998 The far field Oseen velocity expansion. Proc. R. Soc. A 454, 2059–2082.CrossRefGoogle Scholar
Chadwick, E. 2002 A slender-body theory in Oseen flow. Proc. R. Soc. A 458, 2007–2016.CrossRefGoogle Scholar
Chadwick, E. 2005 A slender wing theory in potential flow. Proc. R. Soc. A 461, 415–432.CrossRefGoogle Scholar
Chadwick, E. 2009 A slender body theory in Oseen flow obtained by expanding the Oseenlets in the Green's integral representation. Fluid Dyn. Res. 41, 045508.CrossRefGoogle Scholar
Chadwick, E. & Fishwick, N. 2007 Lift on slender bodies with elliptical cross-section evaluated by using an Oseen flow model. SIAM. J. Appl. Math 67 (5), 1465–1478.Google Scholar
Fishwick, N. J. 2005 Manoeuvring characteristics of slender bodies through fluid. PhD thesis, University of Salford.Google Scholar
Jones, R. T. 1945 Properties of low-aspect-ratio pointed wings at speeds below and above the speed of sound. Tech. Rep. 835. NACA.Google Scholar
Jorgensen, L. H. 1957 Elliptic cones alone and with wings at supersonic speeds. Tech. Rep. 1376. NACA.Google Scholar
Jorgensen, L. H. 1973 Prediction of static aerodynamic characteristics for space-shuttle-like and other bodies at angles of attack from 0 to 180. Tech. Rep. TN D-6996. NASA.Google Scholar
Lighthill, M. J. 1960 Note on the swimming of slender fish. J. Fluid Mech. 9, 305–317.CrossRefGoogle Scholar
Munk, M. M. 1924 The aerodynamic forces on an airship hull. Tech. Rep. 184. NACA.Google Scholar
Newman, J. N. 1977 Marine Hydrodynamics. MIT Press.CrossRefGoogle Scholar
Sigal, A. 1991 Methods of analysis and experiments for missiles with noncircular fuselages. In Tactical Missile Aerodynamics (ed. Mendenhall, M. R.), Ch. 5, pp. 171–223. AIAA.Google Scholar
Simon, J. M. & Blake, W. B. 1999 Missile Datcom: high angle of attack capabilities. AIAA AIAA-99-4258, 1–11.Google Scholar