Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Schematic 3D view of the single-span suspension bridge model in its reference configuration Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Aerodynamic loads acting on the bridge deck section Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Aerodynamic coefficients for the deck section of the Runyang suspension bridge [27,31]: (top) lift and drag and (bottom) aerodynamic moment Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Convergence of the eigenvalues with increasing numbers of trial functions: (top) real parts and (bottom) imaginary parts. The gray lines indicate the symmetric bending–torsional mode while the solid black lines indicate the skew-symmetric mode. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Convergence of the LCO response at the post-critical speed U = 68 m/s, with ζ = 0.5%: (top) torsional rotation φ3 and (center) vertical displacement u 2 at quarter-span, (bottom) FFT of the torsional rotation φ3 at quarter-span Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Variation of the lowest two critical speeds with the initial angle of attack. The gray line indicates the symmetric bending–torsional mode while the solid black line indicates the skew-symmetric mode. The inserts show the skew-symmetric and symmetric bridge mode shapes. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Variations with the wind speed U (top) of the real parts (damping) and (bottom) of the imaginary parts (frequency) at selected initial wind angles of attack, αw=0 deg. The gray lines indicate the symmetric mode while the solid black lines indicate the skew- symmetric mode. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Variations with the wind speed U (top) of the real parts (damping) and (bottom) of the imaginary parts (frequency) at selected initial wind angles of attack, αw=3 deg. The gray lines indicate the symmetric mode while the solid black lines indicate the skew- symmetric mode. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Variations with the wind speed U (top) of the real parts (damping) and (bottom) of the imaginary parts (frequency) at selected initial wind angles of attack, αw=6 deg. The gray lines indicate the symmetric mode while the solid black lines indicate the skew- symmetric mode. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / LCO at the post-flutter speed U = 55 m/s, with ζ = 0.5%. (a) Deck torsional rotation φ3, (b) vertical displacement u 2, and (c) horizontal displacement u 1. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / LCO at the post-flutter speed U = 55 m/s, with ζ = 0.5% (critical mode shape) Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Stable branches (solid lines) and unstable branches (dashed lines) of the bifurcation curves: comparison with direct time integration results (represented by the circles). (Top) Maximum torsional rotation φ3 max and (bottom) maximum vertical displacement u2 max at quarter-span. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Bifurcation curves at selected values of damping ratio ζ. Stable branches (solid lines) and unstable branches (dashed lines). (Top) Maximum torsional rotation φ3 max and (bottom) maximum vertical displacement u2 max at quarter-span. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Bifurcation curves at selected angles of attack α w. Stable branches (solid lines) and unstable branches (dashed lines). (Top) Maximum torsional rotation φ3 max and (bottom) maximum vertical displacement u2 max at quarter-span. Figure Legend:

Date of download: 6/29/2016 Copyright © ASME. All rights reserved. From: Post-Critical Behavior of Suspension Bridges Under Nonlinear Aerodynamic Loading J. Comput. Nonlinear Dynam. 2015;11(1): doi: / Range of stability of LCOs: (top) variation with the damping ratio ζ for αw=0 deg and (bottom) variation with the angle of attack α w for ζ = 0.5% Figure Legend: