Hostname: page-component-745bb68f8f-mzp66 Total loading time: 0 Render date: 2025-01-20T04:02:48.015Z Has data issue: false hasContentIssue false
  • English
  • Français

On the Flow Past a Circular Jet Exhausting at Right Angles from a Flat Plate or Wing

Published online by Cambridge University Press:  04 July 2016

P. T. Wooler
P. T. Wooler*
Affiliation:
formerly British Aircraft Corporation (Operating) Limited, Preston Division, now Northrop Norair, Hawthorne, California
Get access Rights & Permissions [Opens in a new window]

Extract

In recent years there has been considerable interest in the possibility of providing high speed aircraft with the capability of vertical or short take-off and landing (V/STOL). One method for achieving V/STOL is to use lifting engines or fans, the aerodynamic interference effects of which are not yet fully understood. Experimental work on this problem has been done by Jordinson, Otis, Vogler and research workers at the British Aircraft Cor-poration, but no satisfactory theoretical analysis is known. The object of this paper is to put forward a semi-empirical method for predicting the aerodynamic interference of an exhausting jet on a uniform mainstream flow past a wing.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 71 , Issue 675 , March 1967 , pp. 216 - 218
Copyright
Copyright © Royal Aeronautical Society 1967

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.Jordinson, R. Flow in a Jet Directed Normal to the Wind. R and M 3074, 1958.Google Scholar
2.Otis, J. H. Induced Interference Effects on a Four Jet VTOL Configuration with Various Wing Planforms in the Transition Speed Range. NASA TN D-1400, 1962.Google Scholar
3.Vogler, R. D. Surface Pressure Distributions Induced on a Flat Plate by a Cold Air Jet Rising Perpendicularly from the Plate and Normal to a Low-Speed Free-Stream Flow. NASA TN D-1629, March 1963.Google Scholar
4. Unpublished Wind Tunnel Results. British Aircraft Corporation (Operating) Limited, Preston Division.Google Scholar
5.Wyatt, L. A. Some Tests of Ground Effect on Plan-forms Fitted with a Centrally Located Round Lifting Jet. RAE Report No Aero 2826, June 1962.Google Scholar
6.Base, T. E. Lift and Pitching Momentum Increments due to Engines Mounted at an Angle to the Free Stream in a Nacelle or Wing. Bristol Aircraft Aero Note 95, June 1962.Google Scholar
7.Gregory, N. and Raymer, W. G. Wind Tunnel Tests on the Boulton Paul Rectangular Wing (AR2) with Lifting Fan. Series I, ARC 20356, 1958; Series II, ARC 21127, 1959.Google Scholar
8.Falkner, V. M. The Calculation of the Aerodynamic Loading on a Surface of any Shape. ARC R and M 1910, 1943.Google Scholar
9.Richardson, J. R. A Method for Calculating the Lifting Forces on Wings (Unsteady Subsonic and Supersonic Lifting-Surface Theory). ARC R and M 3157, April 1955.Google Scholar