TY - GEN
T1 - Further investigation of vertical stabilizer with passive flow control devices
AU - Ito, Yasushi
AU - Koike, Shunsuke
AU - Murayama, Mitsuhiro
AU - Ichikawa, Yoshiyasu
AU - Nakakita, Kazuyuki
AU - Yamamoto, Kazuomi
AU - Kusunose, Kazuhiro
N1 - Funding Information:
The CFD simulations were performed on the JAXA Supercomputer System generation 2 (JSS2) by Mr. Hiroya Toriida of Ryoyu Systems Co., Ltd. Mr. Tohru Hirai helped us to prepare the geometry of the passive flow control devices. The wind tunnel tests were conducted with the support of the Aerodynamics Research Unit of the Aeronautical Technology Directorate, JAXA.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - This manuscript describes methods to improve the performance of a vertical stabilizer in terms of yawing moment with tip fence, leading-edge vortex generator and delta-shaped vortex generator passive flow control devices, in addition to the midchord vortex generators and dorsal fin discussed in our previous manuscript. A vertical stabilizer designed by ONERA was mounted on the NASA Common Research Model to computationally and experimentally investigate the performance of the flow control devices at several rudder deflection angles. A parametric study of the flow control devices was conducted using wind tunnel tests and computational fluid dynamics simulations, which were also used to understand how vortices generated around the flow control devices interact with the leading-edge separation vortex and boundary layer on the vertical stabilizer and rudder, and how the vortices improve the lateral performance of the vertical stabilizer. Wind tunnel tests were also used to validate the computational results.
AB - This manuscript describes methods to improve the performance of a vertical stabilizer in terms of yawing moment with tip fence, leading-edge vortex generator and delta-shaped vortex generator passive flow control devices, in addition to the midchord vortex generators and dorsal fin discussed in our previous manuscript. A vertical stabilizer designed by ONERA was mounted on the NASA Common Research Model to computationally and experimentally investigate the performance of the flow control devices at several rudder deflection angles. A parametric study of the flow control devices was conducted using wind tunnel tests and computational fluid dynamics simulations, which were also used to understand how vortices generated around the flow control devices interact with the leading-edge separation vortex and boundary layer on the vertical stabilizer and rudder, and how the vortices improve the lateral performance of the vertical stabilizer. Wind tunnel tests were also used to validate the computational results.
UR - https://www.scopus.com/pages/publications/85091900122
U2 - 10.2514/6.2020-1538
DO - 10.2514/6.2020-1538
M3 - Conference contribution
AN - SCOPUS:85091900122
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -