Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-22T10:55:56.526Z Has data issue: false hasContentIssue false
  • English
  • Français

An experimental technique for accurate simulation of the flow field for wing-in-surface-effect craft

Published online by Cambridge University Press:  04 July 2016

A. Sowdon  and
T. Hori
A. Sowdon
Affiliation:
Ship Research Institute Mitaka, Tokyo, Japan
T. Hori
Affiliation:
Ship Research Institute Mitaka, Tokyo, Japan
Get access Rights & Permissions [Opens in a new window]

Summary

This paper describes a simple method to accurately simulate the flow field around a wing in surface effect ship (Wises) model that involves the use of a contraction and a slot to suck the boundary layer from a flat plate. Theoretical aspects of the design are discussed with relation to the required level of suction and the slot width.

The effectiveness is ascertained from measurements of the boundary layer height on the plate through measurement of the mean velocity profile and a reduction in height of 50% was generally observed when suction was used.

Comparison of the forces on a low aspect-ratio wing, obtained from the proposed and the image method, verified the proposed method for wing heights above 2·5% of the mean chord. At lower heights, separation of the boundary layer on the ground plate is thought to have altered the pressure distribution on the wing.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 996 , July 1996 , pp. 215 - 222
Copyright
Copyright © Royal Aeronautical Society 1996 

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

1. Turner, T.R. Endless-belt technique for ground simulation, NASA SP-116, 1966.Google Scholar
2. Staufenbiel, R.W. and Schlichting, U.J. Stability of airplanes in ground effect, J Aircr, 1988, 4, (25), p 289.Google Scholar
3. Sullivan, M.C. Flow breakdown for wings in ground effect, J Aircr, 1978, 12, (15) p 859.Google Scholar
4. Fink, M.P. and Lastinger, J.L. Aerodynamic characteristics of low-aspect-ratio wings in close proximity to the ground, NASA TN D-926, 1961.Google Scholar
5. Katzoff, S. and Sweberg, H.H. Ground Effect on Downwash Angles and Wake Location, NACA R-738, 1941.Google Scholar
6. Turner, T.R. A moving-belt ground plane for wind-tunnel ground simulation and results for 2 jet-flap configurations, NASA TN D- 4228, 1967.Google Scholar
7. Kline, S.J. and Mcclintock, F.A. Describing uncertainties in single-sample experiments, Mech Engineer, 1953.Google Scholar
8. Bryer, D.W. and Pankhurst, A.A. Pressure Probe Methods for Determining Wind Speed and Flow Direction, Her Majesty's Stationary Office, UK, 1971.Google Scholar
9. Maltby, R.L. Flow Visualisation in Wind-Tunnels Using Indicators, Agardograph 70, 1962.Google Scholar
10. Merzkirch, W. Flow Visualisation, Academic Press, 1987.Google Scholar
11. Hirata, N. and Kodama, Y. Flow computation for a three-dimensional wing in ground effect using a multi-block technique, accepted for publication, J Soc of Naval Architects of Japan. Google Scholar