Zobrazeno 1 - 10
of 52
pro vyhledávání: '"Chee Tung"'
Honoring the contributions of one of the field's leading experts, Lu Ting, this indispensable volume contains important new results at the cutting edge of research. A wide variety of significant new analytical and numerical results in critical areas
Autor:
Chee Tung Tai, Hong Heng See
Publikováno v:
Electrophoresis. 40(3)
A new multi-stacking pre-concentration procedure based on field-enhanced sample injection (FESI), field-amplified sample stacking, and transient isotachophoresis was developed and implemented in a compact microchip electrophoresis (MCE) with a double
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::74241b288bdb04958a9337003b880957
https://pubmed.ncbi.nlm.nih.gov/30450561
https://pubmed.ncbi.nlm.nih.gov/30450561
Akademický článek
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Publikováno v:
Journal of the American Helicopter Society. 56:22006-2200619
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::638f769794bd734de2bce9ec7c68b50e
https://doi.org/10.4050/jahs.56.022006
https://doi.org/10.4050/jahs.56.022006
Publikováno v:
Journal of Aircraft. 41:862-869
(AIAA Paper 2003-0048), Journal of Aircraft, Vol. 41, No. 4, pp. 862-969, Jul. - Aug. 2004. The control of compressible dynamic stall using a variable droop leading edge airfoil is described. The leading 25% of a VR-12 airfoil is drooped as it execut
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::271d066046f38963eb2a791a011ba0d7
https://doi.org/10.2514/1.472
https://doi.org/10.2514/1.472
Publikováno v:
Journal of Aircraft. 40:77-85
Dynamic stall calculations were carried out for an airfoil with a dynamically deformed leading-edge (DDLE) shape at a freestream Mach number of 0.3. The surface deformations were done about a baseline NACA 0012 airfoil, effectively increasing the air
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a7fba1a668db4c5d7a49ba7ced09ddd1
https://doi.org/10.2514/2.3060
https://doi.org/10.2514/2.3060
Publikováno v:
Journal of Pressure Vessel Technology. 123:469-474
Analytically predicted results of blade-vortex interaction (BVI) airloads, using the second- generation comprehensive helicopter analysis system (2GCHAS), are presented with the experimental results obtained from the higher-harmonic-control aeroacous
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::f4aea97516f7e4d9203579c87d6e75b9
https://doi.org/10.1115/1.1401025
https://doi.org/10.1115/1.1401025
Publikováno v:
Journal of Aircraft. 35:260-266
An extensive quantity of airload measurements was obtained for a pressure-instrumented model of the BO-105 main rotor for a large number of higher harmonic control settings at Duits-Nederlandse Wind Tunnel. The wake geometry, vortex strength, and vor
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::87a5e8d5b9ae1269a13107c588c849db
https://doi.org/10.2514/2.2293
https://doi.org/10.2514/2.2293
Effect of Wake Structure on Blade - Vortex Interaction Phenomena: Acoustic Prediction and Validation
Publikováno v:
Journal of Aircraft. 35:267-273
During the Higher Harmonic Control Aeroacoustic Rotor Test, extensive measurements of the rotor aerodynamics, the far-field acoustics, the wake geometry, and the blade motion for powered, descent, flight conditions were made. These measurements have
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0e47950ff505d1562811e0e908b99b17
https://doi.org/10.2514/2.2294
https://doi.org/10.2514/2.2294
Publikováno v:
AIAA Journal. 33:289-295
Advanced concepts designed to improve the lift, drag, and pitching moment characteristics of rotor blades have been investigated for the purpose of enhancing rotor maneuver capability. The advantages and disadvantages of these concepts have been eval
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::23efb48053e6998b8777f82d3e4274f5
https://doi.org/10.2514/3.12496
https://doi.org/10.2514/3.12496