TY - GEN
T1 - Effect of flow Reynolds number on the aerodynamics of a novel bionic morphing flap
AU - Akhter, Md Zishan
AU - Riyadh Ali, Ahmed
AU - Omar, Farag Khalifa
N1 - Publisher Copyright:
© 2022 IEEE.
PY - 2022
Y1 - 2022
N2 - The avian wings are characterized by smooth trailing-edge transformations adapting to the flow conditions for optimized flight performance. A novel bionic flap inspired by the avian wings is proposed. It features seamless gradual non-linear spanwise deformations at the trailing-edge. Comprehensive aerodynamic analyses are performed on a 3D S809 airfoil to ascertain the enhancements compared to the - baseline and conventional flap models. The investigation is conducted at the chord-based Reynolds number (Re) values of 0.5 and 1.0 million, with flaps deflected at (β): 10°, subjected to angles of attack (α): 0° & 6°. The influence of flow-incidence angle (α), and Reynolds number (Re) on the aerodynamic performance is carefully studied. The evolution of pressure- and flow- fields, surface-flow, skin-friction, and turbulence, provides insight of the significance of variable spanwise morphing. The proposed spanwise morphing exhibits delayed flow-separation and turbulence suppression over all flow-conditions, compared to the conventional flap.
AB - The avian wings are characterized by smooth trailing-edge transformations adapting to the flow conditions for optimized flight performance. A novel bionic flap inspired by the avian wings is proposed. It features seamless gradual non-linear spanwise deformations at the trailing-edge. Comprehensive aerodynamic analyses are performed on a 3D S809 airfoil to ascertain the enhancements compared to the - baseline and conventional flap models. The investigation is conducted at the chord-based Reynolds number (Re) values of 0.5 and 1.0 million, with flaps deflected at (β): 10°, subjected to angles of attack (α): 0° & 6°. The influence of flow-incidence angle (α), and Reynolds number (Re) on the aerodynamic performance is carefully studied. The evolution of pressure- and flow- fields, surface-flow, skin-friction, and turbulence, provides insight of the significance of variable spanwise morphing. The proposed spanwise morphing exhibits delayed flow-separation and turbulence suppression over all flow-conditions, compared to the conventional flap.
KW - CFD
KW - flow-separation
KW - parabolic flap
KW - S809 airfoil
KW - skin-friction
KW - turbulent kinetic energy
UR - http://www.scopus.com/inward/record.url?scp=85128349001&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85128349001&partnerID=8YFLogxK
U2 - 10.1109/ASET53988.2022.9734807
DO - 10.1109/ASET53988.2022.9734807
M3 - Conference contribution
AN - SCOPUS:85128349001
T3 - 2022 Advances in Science and Engineering Technology International Conferences, ASET 2022
BT - 2022 Advances in Science and Engineering Technology International Conferences, ASET 2022
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2022 Advances in Science and Engineering Technology International Conferences, ASET 2022
Y2 - 21 February 2022 through 24 February 2022
ER -
