Zobrazeno 1 - 9
of 9
pro vyhledávání: '"Zhongguo Niu"'
Publikováno v:
Symmetry, Vol 11, Iss 10, p 1261 (2019)
The symmetric flying wing has a simple structure and a high lift-to-drag ratio. Due to its complicated surface design, the flow field flowing through its surface is also complex and variable, and the three-dimensional effect is obvious. In order to v
Externí odkaz:
https://doaj.org/article/a699379377d94160b1c44492cf9f935d
Publikováno v:
AIAA Journal. 58:61-70
The behaviors of a pulsed microsecond dielectric barrier discharge in quiescent air are diagnosed by schlieren image and particle image velocimetry. Some localized pressure waves are induced by the...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::94f65dd2dd91a6c96cf8bf942b7ac31f
https://doi.org/10.2514/1.j058649
https://doi.org/10.2514/1.j058649
Publikováno v:
Science China Technological Sciences. 58:1949-1955
Spark discharge plasma synthetic jets (SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::175f728e90a945feda6913b9cb4c9669
https://doi.org/10.1007/s11431-015-5881-5
https://doi.org/10.1007/s11431-015-5881-5
Publikováno v:
Plasma Science and Technology. 17:502-509
Experimental investigation of active flow control on the aerodynamic performance of a flying wing is conducted. Subsonic wind tunnel tests are performed using a model of a 35 o swept flying wing with an nanosecond dielectric barrier discharge (NS-DBD
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::39191473deaec432efd29090a4706ee9
https://doi.org/10.1088/1009-0630/17/6/11
https://doi.org/10.1088/1009-0630/17/6/11
Publikováno v:
Chinese Journal of Aeronautics, Vol 28, Iss 2, Pp 377-384 (2015)
Experimental investigation of aerodynamic control on a 35° swept flying wing by means of nanosecond dielectric barrier discharge (NS-DBD) plasma was carried out at subsonic flow speed of 20–40 m/s, corresponding to Reynolds number of 3.1 × 10 5
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::31bb87d860505a3b607e13f3e1b7e722
Publikováno v:
Journal of Aircraft. 50:670-677
b = exposed electrodes width, 1 mm c = clearance distance of consecutive electrodes, 0 mm Cz = aerodynamic force coefficient in z axis,Fz∕ qS Clp = roll moment coefficient caused by plasma actuators d = chord of airfoil, 300 mm e = insulated electr
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::97f90563fde7296dd81a504c95e3316b
https://doi.org/10.2514/1.c031964
https://doi.org/10.2514/1.c031964
The bang-bang optimal control method was proposed for glow discharge plasma actuators, taking account of practical issues, such as limited actuation states with instantaneously varied aerodynamic control performance. Hence, the main contribution of t
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::78c15e4c958603b5b9c24a7aa52cd9b1
Publikováno v:
Proceedings of the 31st Chinese Control Conference; 1/ 1/2012, p4674-4679, 6p
Publikováno v:
Journal of Aircraft. Mar/Apr2013, Vol. 50 Issue 2, p670-677. 8p.