This paper presents a potential flow model for the leading edge vortex over a two-dimensional flat plate at an angle of attack. The paper is an extension of a model by Saffman and Sheffield (1977). A sink has been added in this model in an effort to satisfy the Kutta condition at both the leading edge and the trailing edge of the plate. The introduction of the sink was inspired by the fact that most steady vortices in nature appear in combination with a flow feature which can be interpreted as a sink at their cores when the flow is analyzed in a two-dimensional observation plane. As in the Saffman and Sheffield model, the presence of a vortex results in increased lift; however, in the current model a unique vortex/sink position is found at each angle of attack. A comparison has also been made between the lift and the drag of this model and the corresponding results for two classical solutions of flow over a flat plate: (a) the fully attached flow with the Kutta condition satisfied at the trailing edge only and (b) the Helmholtz solution of fully separated flow.

1.
Brown
C. E.
, and
Michael
W. H.
,
1954
, “
On Slender Delta Wings with Leading Edge Separation
,”
Journal of the Aeronautical Sciences
, Vol.
21
, Oct., pp.
690
694
; also NACA TN-3430, Jan. 1955.
2.
Campbell, J. F., 1975, “Effects of Spanwise Blowing on the Pressure Field and Vortex-Lift Characteristics of a 44° Swept Trapezoidal Wing,” NACA TN D-7907, June.
3.
Huang
M. K.
, and
Chow
C. Y.
,
1982
, “
Trapping of a Free Vortex by Joukowski Airfoils
,”
AIAA Journal
, Vol.
20
, No.
3
, Mar., pp.
292
298
.
4.
Hummel, D., 1978, “On the Vortex Formation Over a Slender Wing at Large Angles of Incidence,” AGARD CP-247, paper no. 15.
5.
Kruppa, E. W., 1977, “A Wind Tunnel Investigation of the Kasper Vortex Concept,” AIAA paper 77–310, Jan.
6.
Mangler, K. W., and Smith, J. H. B., 1957, “A Theory of the Flow past a Slender Wing with Leading Edge Separation,” RAE, Report Aero 2593.
7.
Milne-Thomson, L. M., 1958, Theoretical Aerodynamics, Dover, New York.
8.
Mourtos
N. J.
,
1990
, “
Control of Vortical Separation on a Circular Cone
,”
Aeronautical Journal
, Vol.
94
, pp.
213
219
.
9.
Rossow
V. J.
,
1978
, “
Lift Enhancement by an Externally Trapped Vortex
,”
Journal of Aircraft
, Vol.
15
, No.
9
, pp.
618
625
.
10.
Sacks, A. H., Lundberg, R. E., and Hanson, C. W., 1967, “A Theoretical Investigation of the Aerodynamics of Slender Wing-Body Combinations Exhibiting Leading Edge Separation,” NASA CR-719.
11.
Saffman
P. G.
, and
Sheffield
J. S.
,
1977
, “
Flow over a Wing with an Attached Free Vortex
,”
Studies in Applied Mathematics
, Vol.
57
, pp.
107
117
.
12.
Walton
D.
,
1974
, “
A Brief Wind Tunnel Test of the Kasper Airfoil
,”
Soaring
, Vol.
38
, No.
11
, Nov., pp.
26
27
.
This content is only available via PDF.
You do not currently have access to this content.