Design of active flutter suppression and wind-tunnel tests of a wing model involving a control delay

2015 ◽  
Vol 55 ◽  
pp. 409-427 ◽  
Author(s):  
Rui Huang ◽  
Wenmin Qian ◽  
Haiyan Hu ◽  
Yonghui Zhao
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Tests ◽  
Flutter Suppression ◽  
Control Delay ◽  
Wing Model ◽  
Active Flutter Suppression

scholarly journals Active flutter suppression of a multiple-actuated-wing wind tunnel model

2014 ◽  
Vol 27 (6) ◽  
pp. 1451-1460 ◽  
Author(s):  
Wenmin Qian ◽  
Rui Huang ◽  
Haiyan Hu ◽  
Zhao Yonghui
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Model ◽  
Flutter Suppression ◽  
Tunnel Model ◽  
Active Flutter Suppression

Aeroelastic Wind Tunnel Tests of the RIBES Wing Model

2020 ◽  
pp. 9-28 ◽  
Author(s):  
F. Nicolosi ◽  
V. Cusati ◽  
D. Ciliberti ◽  
Pierluigi Della Vecchia ◽  
S. Corcione
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Tests ◽  
Wing Model

F-16 Flutter Suppression System Investigation Feasibility Study and Wind Tunnel Tests

1982 ◽  
Vol 19 (2) ◽  
pp. 169-175 ◽  
Author(s):  
R. P. Peloubet ◽  
R. L. Haller ◽  
R. M. Bolding
Keyword(s):  
Wind Tunnel ◽  
Feasibility Study ◽  
Wind Tunnel Tests ◽  
Flutter Suppression ◽  
Suppression System

scholarly journals Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward-Swept Wing Model

2021 ◽  
Vol 2021 ◽  
pp. 1-12
Author(s):  
Yan Ouyang ◽  
Kaichun Zeng ◽  
Xiping Kou ◽  
Yingsong Gu ◽  
Zhichun Yang
Keyword(s):  
Wind Tunnel ◽  
Dynamic Pressure ◽  
Wind Tunnel Test ◽  
Swept Wing ◽  
Lattice Method ◽  
Model Calculations ◽  
Wind Tunnel Tests ◽  
Model Based ◽  
Wing Model ◽  
Fidelity Model

The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.

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