TY - GEN
T1 - Experimental and computational investigation of passive surface flow control for aerodynamic efficiency
AU - Chowdhury, Souma
AU - Vani, Divya Ramesh
AU - Maldonado, Victor
AU - Salazar, Matthew
AU - Soujoudi, Ramin
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2017
Y1 - 2017
N2 - A passive surface flow tailoring methodology, inspired by nature, is proposed and studied, under the long-term goal of achieving greater aerodynamic efficiency and stability for wall bounded flows pertinent to systems such as wind turbines and low-speed small unmanned aircraft. In this paper, passive surface features are designed as ridge-lines parallel to the leading edge of the airfoil/wing, with a cross section given by Gaussian curve(s). Subsonic wind tunnel experiments were conducted with a wing section comprised of the symmetric NACA 0012 airfoil; the experiments were run at different angles of attack for incoming Re of about 1e05-2e05. The experiments showed that promising gains can be achieved for lift-to-drag ratios at low angles of attack and in delaying stall angles by using ridges that are close to the leading edge, in comparison to the baseline wing section with no ridges. On the other hand, CFD simulations conducted (using the FLUENT package) on a NACA 4412 airfoil demonstrated that ridges located further away from the leading edge can significantly delay (by > 10% of chord length) flow separation compared to the baseline airfoil with no ridges (for incoming Re of about 2e05).
AB - A passive surface flow tailoring methodology, inspired by nature, is proposed and studied, under the long-term goal of achieving greater aerodynamic efficiency and stability for wall bounded flows pertinent to systems such as wind turbines and low-speed small unmanned aircraft. In this paper, passive surface features are designed as ridge-lines parallel to the leading edge of the airfoil/wing, with a cross section given by Gaussian curve(s). Subsonic wind tunnel experiments were conducted with a wing section comprised of the symmetric NACA 0012 airfoil; the experiments were run at different angles of attack for incoming Re of about 1e05-2e05. The experiments showed that promising gains can be achieved for lift-to-drag ratios at low angles of attack and in delaying stall angles by using ridges that are close to the leading edge, in comparison to the baseline wing section with no ridges. On the other hand, CFD simulations conducted (using the FLUENT package) on a NACA 4412 airfoil demonstrated that ridges located further away from the leading edge can significantly delay (by > 10% of chord length) flow separation compared to the baseline airfoil with no ridges (for incoming Re of about 2e05).
KW - Biomimetic
KW - Computational fluid dynamics
KW - Gaussian ridges
KW - Passive flow control
KW - Wind tunnel experiments
UR - http://www.scopus.com/inward/record.url?scp=85023635482&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85023635482
SN - 9781624105005
T3 - 47th AIAA Fluid Dynamics Conference, 2017
BT - 47th AIAA Fluid Dynamics Conference, 2017
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 47th AIAA Fluid Dynamics Conference, 2017
Y2 - 5 June 2017 through 9 June 2017
ER -