Load distributions on slender delta wings having vortex flow

1977 ◽  
Vol 14 (7) ◽  
pp. 699-702 ◽  
Author(s):  
John Kuhlman
Keyword(s):  
Vortex Flow ◽  
Delta Wings ◽  
Load Distributions

Passive Wingtip Vortex Control by Using Tip-Mounted Half Delta Wings in Ground Effect

2019 ◽  
Vol 142 (2) ◽  
Author(s):  
Anan Lu ◽  
Tim Lee
Keyword(s):  
Vortex Flow ◽  
Ground Effect ◽  
Tip Vortex ◽  
Secondary Vortex ◽  
Flow Properties ◽  
Delta Wings ◽  
Vortex Control ◽  
Physical Mechanisms ◽  
Induced Drag ◽  
Wingtip Vortex

Abstract The ground effect on the wingtip vortex generated by a rectangular semiwing equipped with tip-mounted regular and reverse half delta wings was investigated experimentally. The passive tip vortex control always led to a reduced lift-induced drag as the ground was approached. In close ground proximity, the presence of the corotating ground vortex (GV) added vorticity to the tip vortex while the counter-rotating secondary vortex (SV) negated its vorticity level. The interaction of the GV and SV with the tip vortex and their impact on the lift-induced drag were discussed. Physical mechanisms responsible for the change in the vortex flow properties in ground effect were also provided.

Vortex flow over delta and double-delta wings

1983 ◽  
Vol 20 (9) ◽  
pp. 825-832 ◽  
Author(s):  
H. W. M. Hoeijmakers ◽  
W. Vaatstra ◽  
N. G. Verhaagen
Keyword(s):  
Vortex Flow ◽  
Delta Wings

On the vortex flow over delta and double-delta wings

1982 ◽  
Author(s):  
H. HOEIJMAKERS ◽  
W. VAATSTRA ◽  
N. VERHAAGEN
Keyword(s):  
Vortex Flow ◽  
Delta Wings

Experimental study of vortex flow control on double-delta wings using fillets

1996 ◽  
Vol 33 (4) ◽  
pp. 743-751 ◽  
Author(s):  
Sheshagiri K. Hebbar ◽  
Max F. Platzer ◽  
Abdullah M. Alkhozam
Keyword(s):  
Experimental Study ◽  
Flow Control ◽  
Vortex Flow ◽  
Delta Wings

Some Effects of Design Load Distribution on the Off-design Behaviour of Slender Wings

1965 ◽  
Vol 69 (656) ◽  
pp. 567-572
Author(s):  
L. C. Squire
Keyword(s):  
Economic Performance ◽  
Load Distribution ◽  
Freedom Of Choice ◽  
Delta Wings ◽  
Supersonic Aircraft ◽  
Design Load ◽  
Load Distributions ◽  
Wide Range ◽  
Design Behaviour ◽  
Design Requirements

Summary:In order to trim a supersonic aircraft in the cruise condition it is often most efficient from the viewpoint of economic performance, for which a low drag is necessary, to use a cambered wing. The camber is designed to produce a chosen load distribution, but there is a wide range of suitable distributions. In view of this freedom of choice an investigation of the variation of Cm0 with design load has been made for a particular family of cambered delta wings. The calculations show that from the range of possible design load distributions it should be possible to choose one which results in Cm0 varying approximately in some desired way. Thus In principle It should be possible to choose a load distribution which satisfies the design requirements and results in improved off-design behaviour.

Experimental investigations of the vortex flow on delta wings at high incidence

AIAA Journal ◽  
1992 ◽  
Vol 30 (4) ◽  
pp. 1027-1032 ◽  
Author(s):  
W. H. Stahl ◽  
M. Mahmood ◽  
A. Asghar
Keyword(s):  
Vortex Flow ◽  
Experimental Investigations ◽  
Delta Wings ◽  
High Incidence
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