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pro vyhledávání: '"Wolfgang Geissler"'
Flapping wing efficiency is limited by flow separation effects. The time dependent development of a leading edge vortex (LEV) during rapid pitch-up motion of a retreating helicopter rotor blade is known as dynamic stall vortex. Movement of this vorte
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::f2610fe3949787dd1a259f35e8740161
https://doi.org/10.1016/j.ast.2016.12.008
https://doi.org/10.1016/j.ast.2016.12.008
Autor:
Wolfgang Geissler
Publikováno v:
Aerospace Science and Technology. 14:494-504
Flow control with the aim to avoid or at least delay flow separation and thus enhance performance of rotorcraft has been a topic in various recent investigations. Increase of maximum lift combined with drag reduction in steady applications as well as
Publikováno v:
Journal of Aircraft. 45:1334-1343
Effects due to hydrophilic surfaces are investigated on an airfoil by means of both experimental and numerical approaches. Boundary-layer velocity profiles are measured by embedded laser Doppler velocimetry along the NACA0012 airfoil upper-side surfa
Autor:
Markus Maurer, Wolfgang Geißler
Publikováno v:
ATZextra worldwide. 12:148-151
Autor:
Wolfgang Geissler, Hartmut Haselmeyer
Publikováno v:
Aerospace Science and Technology. 10:590-600
In a 2003 test campaign in the DLR-VAG test stand unsteady pressure distributions during dynamic stall have been measured on a 2D-wing model with OA312 airfoil section. To investigate the effect of transition on dynamic stall onset different tripping
It has been recognized by the European Union (EU) that the survival of the Aeronautical Industries of Europe in the highly competitive World Aviation Market is strongly dependent on such factors as time-to-market of a new or derivative aircraft and o
Autor:
Holger Mai, Klaus de Groot, Wolfgang Geißler, Guido Dietz, Kai Richter, Johannes Bosbach, Hughes Richard
Publikováno v:
Scopus-Elsevier
A new concept of passive dynamic-stall control was developed and tested on an OA209 rotorcraft airfoil during two wind-tunnel test campains in 2004 and 2005. Small vortex generators are mounted at the leading edge of the rotor blade. At low incidence
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::cd12fa838c92e67b5ea889ab883b13dc
https://elib.dlr.de/53998/
https://elib.dlr.de/53998/
Publikováno v:
Wind Energy ISBN: 9783540338659
Dynamic Stall is a flow phenomenon which occurs on helicopter rotor blades during forward flight mainly on the retreating side of the rotor disc. This phenomenon limits the speed of the helicopter and its manoeuvrability. Strong excursions in drag an
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::12f379a001941e04e4824dbfdbad7ecf
https://doi.org/10.1007/978-3-540-33866-6_36
https://doi.org/10.1007/978-3-540-33866-6_36
Publikováno v:
Measurement Science and Technology
Measurement Science and Technology, 2006, 17, pp.1652-1658
Measurement Science and Technology, 2006, 17, pp.1652-1658
Studies of the boundary layer profile and of the characteristics of the flow velocity distribution close to the leading edge of a helicopter blade profile were conducted using embedded laser Doppler velocimetry (ELDV) and stereo particle image veloci
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::d346ce7971b3822d049ccbe02ffd239e
https://hal.archives-ouvertes.fr/hal-00091853
https://hal.archives-ouvertes.fr/hal-00091853
Autor:
Wolfgang Geissler, Stefan Koch
Publikováno v:
IUTAM Symposium Transsonicum IV ISBN: 9789401039987
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6d9ba37e89395fb8a42f22a6113160d2
https://doi.org/10.1007/978-94-010-0017-8_46
https://doi.org/10.1007/978-94-010-0017-8_46