Author: Z. Shi
Publisher:
ISBN:
Category :
Languages : en
Pages : 11

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Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781731351593
Category :
Languages : en
Pages : 162

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The vortical flow over a delta wing contributes an important part of the lift - the so called nonlinear lift. Controlling this vortical flow with its favorable influence would enhance aircraft maneuverability at high angle of attack. Several previous studies have shown that control of the vortical flow field is possible through the use of blowing jets. The present experimental research studies vortical flow control by applying a new blowing scheme to the rounded leading edge of a delta wing; this blowing scheme is called Tangential Leading Edge Blowing (TLEB). Vortical flow response both to steady blowing and to unsteady blowing is investigated. It is found that TLEB can redevelop stable, strong vortices even in the post-stall angle of attack regime. Analysis of the steady data shows that the effect of leading edge blowing can be interpreted as an effective change in angle of attack. The examination of the fundamental time scales for vortical flow re-organization after the application of blowing for different initial states of the flow field is studied. Different time scales for flow re-organization are shown to depend upon the effective angle of attack. A faster response time can be achieved at angles of attack beyond stall by a suitable choice of the initial blowing momentum strength. Consequently, TLEB shows the potential of controlling the vortical flow over a wide range of angles of attack; i.e., in both for pre-stall and post-stall conditions. Lee, K. T. and Roberts, Leonard BLOWING; DELTA WINGS; FLOW DISTRIBUTION; LEADING EDGES; VORTICES; AIRCRAFT MANEUVERS; ANGLE OF ATTACK; MOMENTUM; NONLINEARITY; STABILITY...

Author: David Yeh
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 154

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Author: Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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Author: Chih Shih
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 106

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Author: K. T. Lee
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 178

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Author: Chester J. GABRIEL
Publisher:
ISBN:
Category :
Languages : en
Pages : 95

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A wind tunnel investigation was made of the effects of leading edge blowing jets, in the plane of the planform and directed away from the wing, upon the lift, drag, and pitching moment of a 76 degree delta wing of aspect ratio one. A theory for the lift of a flat plate delta is presented and compared with the experimental data. It was found that jet outlet velocity/free-stream velocity is a better parameter than momentum coefficient for the analysis of lift data with the type of blowing jet configuration used. Lift coefficient increased appreciably with blowing at low values of the parameters, and then tended to level off as blowing was increased. At low angles of attack, the only additional drag induced by blowing was the momentum drag due to the rearward thrust of the jets. It was found that such blowing reduced the stability of the wing. (Author).

Author: W. J. G. Trebble
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 19

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Author: Kenneth P. Iwanski
Publisher:
ISBN:
Category :
Languages : en
Pages : 44

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Author: Stanford University. Department of Aeronautics and Astronautics
Publisher:
ISBN:
Category :
Languages : en
Pages : 396

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