Computational study of incipient leading-edge separation on a supersonic delta wing

1992 ◽  
Vol 29 (2) ◽  
pp. 203-209 ◽  
Author(s):  
S. Naomi McMillin ◽  
James L. Pittman ◽  
James L. Thomas
Keyword(s):  
Delta Wing ◽  
Computational Study ◽  
Leading Edge ◽  
Edge Separation

A Note on the Vorticity Distribution on the Surface of Slender Delta Wings with Leading Edge Separation

1961 ◽  
Vol 65 (603) ◽  
pp. 195-198 ◽  
Author(s):  
B. J. Elle ◽  
J. P. Jones
Keyword(s):  
Experimental Evidence ◽  
Delta Wing ◽  
Leading Edge ◽  
Water Tunnel ◽  
Delta Wings ◽  
Vorticity Distribution ◽  
Edge Separation

A description is given of the distribution of vorticity in the surface of thin wings with large leading edge sweep. Although the delta wing is chosen as the basic plan form the deductions are general and applicable to other types of wing. The conclusions are illustrated with experimental evidence from a water tunnel.

Flow Regimes over Delta Wings at Supersonic and Hypersonic Speeds

1976 ◽  
Vol 27 (1) ◽  
pp. 1-14 ◽  
Author(s):  
L C Squire
Keyword(s):  
Shock Layer ◽  
Delta Wing ◽  
Leading Edge ◽  
Flow Regimes ◽  
Lower Surface ◽  
Delta Wings ◽  
Thin Shock Layer ◽  
Wide Range ◽  
Wing Sweep ◽  
Edge Separation

SummaryThis paper concerns the boundaries between flow regimes for sharp-edged delta wings in supersonic flow and the relation of some predictions of thin-shock-layer theory to these boundaries. In particular, it is shown that the theory predicts that the attachment lines on the lower surface of a thin delta wing at supersonic speeds suddenly jump from just inboard of the leading edges to the centre line in certain flight conditions. In general there is close agreement between the conditions for this jump and the flight conditions corresponding to the change-over from attached flow to the leading-edge separation on the upper surface. Since the movement of the attachment lines on the lower surface must change the position of the sonic line and the nature of the expansion around the edge, it is suggested that the two phenomena are directly related. Thus thin-shock-layer theory can be used to establish the boundaries of the various flow regimes for a wide range of Mach number, incidence and wing sweep. The theory can also be used to predict the effects of wing thickness on leading-edge separation, but here the experimental data is very sparse and somewhat contradictory, so the value of the prediction in the case of thickness requires further investigation.

A computational study of laminar-flow secondary separation on a slender delta wing

2018 ◽  
Vol 122 (1256) ◽  
pp. 1654-1672 ◽  
Author(s):  
I. P. Jones ◽  
N. Riley
Keyword(s):  
Boundary Layer ◽  
Laminar Flow ◽  
Delta Wing ◽  
Computational Study ◽  
Leading Edge ◽  
Vortex Sheet ◽  
Flow Measurements ◽  
Leading Edge Vortex ◽  
Edge Vortex ◽  
Secondary Separation

ABSTRACTThe laminar flow over a slender delta wing at incidence has been extensively studied both experimentally and theoretically using vortex sheet methods. These vortex sheet methods have generally been successful apart from the prediction of the secondary boundary-layer separation induced by the primary vortex. This paper revisits the problem using computational fluid dynamics (CFD) and focusses on the effects of the secondary flow separation. The modelling approach is briefly summarised, and the results are compared with flow measurements and results from vortex sheet methods. The computations show very good agreement with measurements for the surface pressures and total head contours. The results help to understand the complex structure of the leading edge vortex flow, and the associated secondary separation of the boundary layer. They indicate that inviscid mechanisms dominate the larger scale features, and highlight a possible mechanism for the development of an instability in the leading edge vortex sheet.

Spanwise cambered delta wing with leading-edge separation

1977 ◽  
Vol 14 (3) ◽  
pp. 276-282 ◽  
Author(s):  
Joe Fernandez ◽  
V. S. Holla
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Edge Separation
Sign in / Sign up

Export Citation Format

Share Document