Zobrazeno 1 - 9
of 9
pro vyhledávání: '"Till Schwermer"'
Autor:
Armin Weiss, Christoph B. Merz, Till Schwermer, Anthony Donald Gardner, C. Christian Wolf, Markus Raffel, Johannes N. Braukmann
Publikováno v:
AIAA Journal. 55:1753-1756
RAFFEL and Merz [1] demonstrated the feasibility of unsteady boundary-layer transition detection by differential infrared thermography (DIT), a method whereby the difference of two sequentially recorded infrared images is analyzed to extract the poin
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::67899acc5563635327e0653b5dc88b1d
https://doi.org/10.2514/1.j055452
https://doi.org/10.2514/1.j055452
A rotor test facility was developed to investigate dynamic stall under optimized boundary conditions compared to conventional hover chambers. lt features a defined axial inflow, reduction of ground effect and recirculation of the rotor wake and good
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::a7d070dc81143843a0f2a44330732016
https://elib.dlr.de/111646/
https://elib.dlr.de/111646/
Laminar-turbulent boundary-layer transition is investigated on the suction side of Mach-scaled helicopter rotor blades in climb and analyzed in view of the effect of rotational forces. Transition p...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::97e62d3938df671f1cf60799dbda3f1d
https://elib.dlr.de/119088/
https://elib.dlr.de/119088/
The tip vortex system downstream of a four-bladed instrumented rotor was investigated experimentally through the application of stereoscopic particle image velocimetry (PIV). A dynamic stall test case was facilitated by a high cyclic pitch setting of
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::26f2693af1302f7b2e7ae7b35422bbe6
https://elib.dlr.de/127163/
https://elib.dlr.de/127163/
Autor:
Till Schwermer, Andreas Goerttler, Markus Raffel, Johannes N. Braukmann, Anthony Donald Gardner
Publikováno v:
Scopus-Elsevier
The blade-tip vortex of a rotating and pitching DSA-9A blade was investigated numerically and experimentally. Numerical computations were performed using DLR, German Aerospace Center’s finite volum...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::c7f803491542834273f0a52b08c3cfa4
https://doi.org/10.2514/1.c034693
https://doi.org/10.2514/1.c034693
Autor:
Armin Weiss, Markus Raffel, Christian Klein, Daisuke Yorita, Reinhard Geisler, Till Schwermer, Ulrich Henne
A pressure-sensitive paint (PSP) system is presented to measure global surface pressures on fast rotating blades. It is dedicated to solve the problem of blurred image data employing the single-shot lifetime method. The efficient blur reduction capab
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::7e1a51be26137032ed67f7f05542883f
https://elib.dlr.de/118641/
https://elib.dlr.de/118641/
Publikováno v:
Notes on Numerical Fluid Mechanics and Multidisciplinary Design ISBN: 9783319272788
The flight envelope of modern helicopters is limited due to unsteady flow phenomena such as dynamic stall. Most investigations regarding this topic, both experimental and numerical, were done on pitching two-dimensional airfoils. Therefore, it is of
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::905fec5be8966f943673315665f81f3b
https://doi.org/10.1007/978-3-319-27279-5_58
https://doi.org/10.1007/978-3-319-27279-5_58
Publikováno v:
Experiments in Fluids. 56
Differential infrared thermography (DIT) was investigated and applied for the detection of unsteady boundary layer transition locations on a pitching airfoil and on a rotating blade under cyclic pitch. DIT is based on image intensity differences betw
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::059a1d57f4ba188378e60905183b12d0
https://doi.org/10.1007/s00348-015-1905-y
https://doi.org/10.1007/s00348-015-1905-y
Publikováno v:
Scopus-Elsevier
Numerical investigations of three-dimensional dynamic stall on a two-bladed Mach-scaled rotor (R = 0.65m, Ma75 = 0.21, Re75 = 3.5 × 105) with 1/rev cyclic pitch control are presented and compared to experimental surface pressure and PIV data. In add
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::f9eac380f741f2f993f5c85155cf1482
http://www.scopus.com/inward/record.url?eid=2-s2.0-85052509182&partnerID=MN8TOARS
http://www.scopus.com/inward/record.url?eid=2-s2.0-85052509182&partnerID=MN8TOARS