By Daniel Reckzeh, Heinz Hansen (auth.), Prof. Dr. Hans-Josef Rath, Carsten Holze, Dr. Hans-Joachim Heinemann, Rolf Henke, Professor Dr. Heinz Hönlinger (eds.)
ISBN-10: 3540332863
ISBN-13: 9783540332862
ISBN-10: 3540332871
ISBN-13: 9783540332879
This quantity includes the contributions to the 14. Symposium of the STAB (German Aerospace Aerodynamics Association). during this organization all these German scientists and engineers from universities, examine institutions and are concerned, who're doing examine and venture paintings in numerical and experimental fluid mechanics and aerodynamics, commonly for aerospace yet for different functions, too. some of the contributions are providing effects from nationwide and ecu neighborhood subsidized tasks. the quantity provides a large evaluation over the continued paintings during this box in Germany, with the themes being high-aspect ratio wings, low aspect-ratio wings, bluff our bodies, laminar movement regulate and transition, lively stream keep an eye on, hypersonic flows, aeroelasticity, aeroacoustics, mathematical basics/ numerical simulation, actual basics, and facilities.
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Additional resources for New Results in Numerical and Experimental Fluid Mechanics V: Contributions to the 14th STAB/DGLR Symposium Bremen, Germany 2004
Sample text
Kauertz, G. Neiiwerth, and R. SchoU 4 Results The PIV measurements provide velocity distributions containing the vortices of the wing. 0 have been investigated. At each position measurements without fin and with the fin in two positions have been made as described in section 2. From the velocity distributions vorticity has been calculated as well as induced rolling moments on a following wing using strip theory. The induced rolling moments have been computed according to bF/2 bp/z p2- / 2-1: arctanijp-jy'dy', (1) OF -bF/2 with hp being the span of the following wing and Vz/uoo the induced angle of attack on the wing.
5 yields a decrease of the viscous core radius of the WTV and OFV-ONV of 32% and 34%, respectively. 5% for the OFV-ONV. A parameter, Effect of Differential Flap Settings on the Wake Vortex Evolution 29 which permits to judge the benefit brought by the DFS, is the strength of the wake G* = -fr, where TQ is the initial circulation for an elliptical loaded wing, [4]. 2, respectively. The 32''/8° configuration shows a strong decrease of about 60% in the OFV-ONV strength ( ^ ^ r g>"i-'>f), as expected from the limited flap deflection.
02 in vertical direction was used. 1 Results and Discussion The Evolution of the Wake The normalized axial vorticity ^ —Wx • {b/2)/Uoo is used to identify significant vortical structures and to define their location on each cross flow plane. The coordinates y and z are normalized using the wing half span 6/2. 37. The wjJse, in its near field, consists basically of six major vortices: the wing tip vortex (WTV), the outboard flap vortex (OFV), the outboard nacelle vortex (ONV), the inboard nacelle vortex (INV), the counter rotating horizontal tail tip vortex (HTV) and the wing fuselage junction vortex (WFV).
New Results in Numerical and Experimental Fluid Mechanics V: Contributions to the 14th STAB/DGLR Symposium Bremen, Germany 2004 by Daniel Reckzeh, Heinz Hansen (auth.), Prof. Dr. Hans-Josef Rath, Carsten Holze, Dr. Hans-Joachim Heinemann, Rolf Henke, Professor Dr. Heinz Hönlinger (eds.)
by Paul
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