Lift enhancement of a thick delta wing using rotational leading edges

2002 ◽  
Author(s):  
D. Azuma ◽  
Y. Nakamura
Keyword(s):  
Delta Wing ◽  
Lift Enhancement ◽  
Leading Edges

On the Effect of the Incident Mach’s Wave on the Pulsation Level in Boundary Layer of the Plane Delta Wing

2014 ◽  
Vol 9 (1) ◽  
pp. 29-38
Author(s):  
Aleksandr Vaganov ◽  
Yuri Yermolaev ◽  
Gleb Kolosov ◽  
Aleksandr Kosinov ◽  
Aleksandra Panina ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mass Flow ◽  
Delta Wing ◽  
Level Fluctuation ◽  
Flow Pulsation ◽  
Flow Conditions ◽  
Wing Model ◽  
Maximum Value ◽  
Leading Edges ◽  
High Level

The experimental results of high level fluctuation excitation by external Mach’s wave in the boundary layer of delta wing model with blunt leading edges at Mach numbers M = 2, 2.5, 4 are presented. The exitation areas and mass flow pulsation levels in the conditions of subsonic, sonic and supersonic leading edges have been defined. It was found that the maximum value of the pulsations is 12–15 % and varies only slightly from the flow conditions around of the delta wing

The Lift of Twisted and Cambered Wings in Supersonic Flow

1955 ◽  
Vol 6 (2) ◽  
pp. 149-163 ◽  
Author(s):  
G. N. Lance
Keyword(s):  
Integral Equation ◽  
Velocity Potential ◽  
Free Stream ◽  
Delta Wing ◽  
Complete Solution ◽  
Symmetric Potential ◽  
Leading Edges ◽  
Limiting Case ◽  
The Given ◽  
Stream Direction

SummaryA generalised conical flow theory is used to deduce an integral equation relating the velocity potential on a delta wing (with subsonic leading edges) to the given downwash distribution over the wing. The complete solution of this integral equation is derived. This complete solution is composed of two parts, one being symmetric and the other anti-symmetric with respect to the span wise co-ordinate; each part represents a velocity potential. For example, if y is the spanwise co-ordinate and x is measured in the free stream direction, then a downwash of the form w= - α11 Ux|y| is symmetric and will give rise to a symmetric potential, whereas w= - α11 Ux|y| sgn y is anti-symmetric and gives rise to an anti-symmetric potential. The velocity potentials of such flows are given in the form of Tables for all downwashes up to and including homogenous cubics in the spanwise and streamwise co-ordinates. Table III gives similar formulae in the limiting case when the leading edges become transonic; these are compared with results given elsewhere and serve as a check on the results of Tables I and II.

From Ship-Accompanying Waves to Shock Waves of Supersonic Aeroplanes

1962 ◽  
Vol 66 (615) ◽  
pp. 163-176
Author(s):  
Robert G. Legendre
Keyword(s):  
Shock Waves ◽  
Delta Wing ◽  
Good Reason ◽  
Point Of View ◽  
Memorial Lecture ◽  
Vortex Sheets ◽  
Leading Edges

When I was invited to deliver the Lanchester Memorial lecture, I wondered why the great honour of being the first Frenchman selected for the celebration of the deeds of a great engineer was conferred on me. However, I am well aware that the Council of the Royal Aeronautical Society cannot make a mistake and there is good reason to choose, after so greatly famed professors, an engineer of the French Navy to illustrate, using a slightly different point of view, the influence of Lanchester on the development of aeronautics. This way, I do not have to apologise for a possible inadequacy which then would not be my own responsibility. I have only to do my best, so as not to betray the confidence of the Society. Answering so plainly this first question, I had to find out how to fulfil my task. Possibly, my contribution to the intrepretation of the vortex sheets starting from the thin leading edges of a delta wing is more in the Lanchester line of thought than it is an extension of Prandtl’s inferences.

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