Table S1. Results of the MANOVA to test shape difference between groups.

Non-allometric wingshape component
df / F / p
Status / 1,462 / 0.40 / 0.920
Period / 1,462 / 1.64 / 0.135
Status x period / 1,462 / 0.51 / 0.807
Allometric wingshape component
df / F / p
Status / 1,462 / 0.02 / 0.900
Period / 1,462 / 4.76 / 0.031
Status x period / 1,462 / 0.24 / 0.633

Table S2. Descriptive statistics (a), covariance (b) and correlation matrices (c) of the studied traits.

(a)

N / Min / Max / Mean / SD / SE
Flight speed (cm/s) / 466 / 6.83 / 75.00 / 25.92 / 11.6 / 0.54
Flight endurance (s) / 466 / 11.00 / 389.00 / 81.93 / 49.81 / 2.31
Relative fat content (µg/mg body mass) / 466 / 7.73 / 33.84 / 15.37 / 4.71 / 0.22
Flight muscle ratio (µg/mg body mass) / 466 / 21.20 / 49.10 / 34.40 / 4.46 / 0.21
Wing centroid size (pixel) / 466 / 3352.50 / 3937.31 / 3672.76 / 87.79 / 4.07
Body mass (mg) / 466 / 44.91 / 65.85 / 54.50 / 3.39 / 0.16
Wing loading (mg/mm2) / 466 / 0.54 / 0.73 / 0.64 / 0.03 / 1.40E-03
Allometric wing shape / 466 / -0.02 / 0.02 / -8.37E-11 / 0.01 / 2.68E-04
Non-allometric wing shape PC1 / 466 / -0.04 / 0.03 / -5.2E-11 / 0.01 / 4.55E-04
Non-allometric wing shape PC2 / 466 / -0.02 / 0.02 / 1.33E-10 / 0.01 / 2.55E-04
(b)
Covariance / Speed / Endurance / Fat content / FMR / Centroid size / Body mass / Wing loading / Allo PC / Non-alloPC1 / Non-alloPC2
Speed / 134.56 / -92.09 / -5.7 / -0.45 / 60.08 / -0.71 / -0.03 / 5.75E-03 / 4.09E-03 / 1.67E-05
Endurance / -92.09 / 2480.7 / -1.19 / 14.97 / 133.25 / -5.97 / -0.02 / 0.02 / 7.44E-03 / 0.02
Fat content / -5.7 / -1.19 / 22.14 / 9.35 / -4.62 / 0.96 / 0.02 / -4.76E-03 / -4.18E-03 / -1.86E-03
FMR / -0.45 / 14.97 / 9.35 / 19.91 / 22.21 / 0.66 / -0.01 / -1.44E-03 / -3.50E-05 / -2.80E-03
Centroid size / 60.08 / 133.25 / -4.62 / 22.21 / 7707.48 / 10.73 / -0.15 / 0.17 / 1.42E-03 / -3.52E-04
Body mass / -0.71 / -5.97 / 0.96 / 0.66 / 10.73 / 11.51 / 0.01 / -1.13E-03 / -1.60E-03 / 4.90E-04
Wing loading / -0.03 / -0.02 / 0.02 / -0.01 / -0.15 / 0.01 / 9.07E-04 / -8.50E-06 / -7.70E-06 / -3.28E-05
Allo / 5.75E-03 / 0.02 / 4.76E-03 / -1.44E-03 / 0.17 / -1.13E-03 / -8.50E-06 / 3.34E-05 / 1.98E-05 / 1.20E-05
Non-alloPC1 / 4.10E-03 / 7.44E-03 / 4.18E-03 / -3.51E-05 / 1.42E-02 / -1.60E-03 / -7.70E-06 / 1.98E-05 / 9.64E-05 / -1.58E-12
Non-alloPC2 / 1.67E-05 / 0.02 / -1.86E-03 / -2.80E-03 / -3.50E-04 / 4.90E-04 / -3.28E-05 / 1.20E-05 / -1.58E-12 / 3.02E-05

(c)

Correlation / Speed / Endurance / Fat content / FMR / Centroid size / Body mass / Wing loading / Allo / Non-alloPC1 / Non-alloPC2
Speed / 1.00 / -0.16 / -0.10 / -0.01 / 0.06 / -0.02 / -0.08 / 0.09 / 0.04 / 0.00
Endurance / -0.16 / 1.00 / -0.01 / 0.07 / 0.03 / -0.04 / -0.01 / 0.06 / 0.02 / 0.07
Fat content / -0.10 / -0.01 / 1.00 / 0.45 / -0.01 / 0.06 / 0.11 / -0.18 / -0.09 / -0.07
FMR / -0.01 / 0.07 / 0.45 / 1.00 / 0.06 / 0.04 / -0.05 / -0.06 / -8.00E-04 / -0.11
Centroid size / 0.06 / 0.03 / -0.01 / 0.06 / 1.00 / 0.04 / -0.06 / 0.34 / 1.65E-03 / -7.30E-04
Body mass / -0.02 / -0.04 / 0.06 / 0.04 / 0.04 / 1.00 / 0.10 / -0.06 / -0.05 / 0.03
Wing loading / -0.08 / -0.01 / 0.11 / -0.05 / -0.06 / 0.10 / 1.00 / -0.05 / -0.03 / -0.20
Allo / 0.09 / 0.06 / -0.18 / -0.06 / 0.34 / -0.06 / -0.05 / 1.00 / 0.35 / 0.38
Non-alloPC1 / 0.04 / 0.02 / -0.09 / -8.00E-04 / 1.64E-03 / -0.05 / -0.03 / 0.35 / 1.00 / -2.92E-08
Non-alloPC2 / 2.62E-04 / 0.07 / -0.07 / -0.11 / -7.29E-04 / 0.03 / -0.20 / 0.38 / -2.92E-08 / 1.00

Figure S1. Schematic figure of the flight tube to quantify flight performance. The transparent Plexiglas flight tube (height: 200 cm, diameter: 20 cm) was placed in a 43° angle and was fixed for stabilization. The top of the tube was covered with a transparent Plexiglas lid and a 500 W halogen lamp was used as a light source above the tube.

Figure S2. The left hind wing of a C. viridis male with the 17 digitalized landmarks: (1) the intersection of the first antenodal vein and the leading edge of the wing; (2) the intersection of the second antenodal vein and the leading edge of the wing; (3) the nodus; (4) the proximal end of the pterostigma; (5) the distal end of the pterostigma; (6) the distal end of the pterostigma supplemented with two cells; (7) the intersection of the R1 vein and the leading edge of the wing; (8) the most distal point of the wing; (9) the intersection of the R3 vein and the leading edge of the wing; (10) the intersection of the IR3 vein and the leading edge of the wing supplemented with one cell; (11) the intersection of the R4 vein and the leading edge of the wing; (12) the intersection of the MA vein and the leading edge of the wing; (13) the intersection of the Cup vein and the leading edge of the wing; (14) the intersection of the crossvein from the nodus to the opposite side of the leading edge of the wing minus one cell; (15) the intersection of the crossvein under the arculus and the leading edge of the wing; (16) the intersection of the crossvein after the arculus and the leading edge of the wing; (17) the point of the edge of the wing opposite to landmark one. Landmark 8 and 14 are semi-landmarks.

Figure S3. Principal component analysis (PCA) on the non-allometric wing shape component. Deformation grid represents wing shape of extreme individuals on PC1.