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. 2022 Feb 2;12:1793. doi: 10.1038/s41598-022-05739-1

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© The Author(s) 2022

Open Access This article is licensed under a Creative Commons Attribution 4.0 International License, which permits use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons licence, and indicate if changes were made. The images or other third party material in this article are included in the article's Creative Commons licence, unless indicated otherwise in a credit line to the material. If material is not included in the article's Creative Commons licence and your intended use is not permitted by statutory regulation or exceeds the permitted use, you will need to obtain permission directly from the copyright holder. To view a copy of this licence, visit http://creativecommons.org/licenses/by/4.0/.

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An illustration of the tracked body points and the metrics calculated for each glide. (a) Illustration showing the five body points tracked per frame for each glide. (b) The three axes about which the lizard can reorient in flight. Longitudinal axis (lo) about which the lizard rolls. Transverse axis (ta) about which the lizard changes pitch. Vertical axis (ve) about which the lizard changes yaw. (c) Illustration showing the airfoil area used to calculate the aerodynamic force coefficients. The area was calculated by fitting a plane to the 17 3D points tracked around the lizard in a single frame during the glide when the patagium was completely stretched open. (d) Yaw angle is the rotation about the (ve) from the X–Z plane, positive yaw is to the lizard’s left. (e) Pitch angle is the rotation about the (ta) from the X–Y plane, positive pitch raises the head upward. (f) Roll angle is the rotation about the (lo) from the Z–Y plane, positive roll raises the left-wing tip. (g) Angle of attack (AoA) is the angle made by the airfoil surface relative to the direction of motion (airflow), positive AoA is counterclockwise. (h) Camber is the convexity (concave down) of the airfoil from the leading to the trailing edge. The formula provided shows the calculation for % camber. (i) Dihedral angle is the average of the upward angle made by either side of the wing with the X–Y plane.