Experimental and Numerical Investigation of the Vortex Flow Over a Sharp Edged Delta Wing; with and Without Sideslip PDF Download
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Author: S. H. J. Naarding
Publisher:
ISBN:
Category :
Languages : en
Pages : 224
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Author: S. H. J. Naarding
Publisher:
ISBN:
Category :
Languages : en
Pages : 224
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Author: J. E. J. Maseland
Publisher:
ISBN:
Category :
Languages : nl
Pages : 95
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 464
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Author: N. G. Verhaagen
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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A wind-tunnel investigation was performed to study, by employing a laserlight-sheet and oil-flow visualization technique, the flow above and behind a sharp-edge 76 deg, delta wing and two sharp-edged double-delta wing models (76/60 and 76/40 deg., kink at midcord). In addition, balance measurements were performed to determine lift, drag and pitching moment. The tests were carried out for angles of attack from 5 to 25 deg. and at a free-stream velocity of 30 m/sec, corresponding to a Reynolds number of 1400000 x 10 to the 6th power, based on centerline chord. Above both double-delta wings a single-branched strake vortex is formed fed by vorticity from the strake leading edge. Downstream of the leading-edge kink a wing vortex is formed which is conjectured to be single-branched at about 5 deg, angle of attack and double branched at angles of 10 deg., an beyond. The flow pattern downstream of the trailing edge of the 76/60 deg. double-delta wing has been observed to be similar to that behind the delta wing. Above the 76/40 deg. double-delta wing breakdown of both the wing and strake vortices took place ahead of the trailing edge. (Author).
Author: Raymond E. Gordnier
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 50
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This report presents computations of the flowfield around an 80 degree sweep delta wing undergoing a constant roll-rate maneuver from 0 to 45 degrees. The governing equations for the problem are the unsteady, three- dimensional Navier-Stokes equations. The equations are solved using the implicit, approximately-factored algorithm of Beam-Warming. Fixed roll angle results are also presented and compared with experimental measurements to demonstrate the ability of the numerical technique to accurately capture the flowfield around a rolled delta wing. The dynamic behaviors of the vortex position and strength, as well as their corresponding effect on surface pressure, lift and roll moment, are described. A simple, quasi-static explanation of these vortex behaviors based on effective angle-of-attack and sideslip angle is proposed ... Delta wing roll, Vortex dynamics, Vortical flow, Unsteady maneuver.
Author: W. J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages : 63
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
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Author: Xing Z. Huang
Publisher: Springer Verlag
ISBN: 9781402093326
Category : Science
Languages : en
Pages : 516
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The book discusses the behavior of vortices over sharp and highly swept wing configurations used for current and future military aircraft. Special attention is paid to the effects of critical flow phenomenon such as vortex breakdown occuring at high angles of attack or high angular rates. The wind tunnel experiments conducted on delta-wing configurations in wind tunnels in Canada, Europe, Russia and the United States are given in eight chapters. The experiments provide an extended data base that gives insight into the effects of the angle of attack, angular rate, Reynolds number and Mach number on the behavior of vortices over several slender delta wings in stationary and instationary flights. A critical assessment is given in a separated chapter of the available experimental data bases and out of these data, one and the same data set is selected for the validation and verification of analytical and numerical solutions.Comprehansive computational results are given in another ten chapters. Steady-state and time-accurate solutions for the steady and unsteady flow over the selected delta-wing configuration are discussed. These solutions are generated using structured and unstructured grid methods.The analytical solutions for the flow over a delta wing are discussed and compared with experimental data in three more chapters.In the final chapter a validation and verification of the analytical and CFD solutions is given.
Author: W. Stahl
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 654
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