Abstract
The aerodynamic characteristics of airfoils have been researched in higher Reynolds-number ranges more than 106 , in a historic context closely related with the developments of airplanes and fluid machineries in the last century. However, our knowledge is not enough at low and middle Reynolds-number ranges. So, in the present study, we investigate three kinds of airfoils; namely, an iNACA0015 (the NACA0015 placed back to front) which was proposed as a high-performance airfoil for low Reynolds number and such two basic airfoils as a NACA0015 and a flat plate, in a very-low-Reynolds-number range of Re = 1.0×102 – 8.0×102 , using water-tank experiments and three-dimensional computations. As a result, we have revealed the effects of attack angle α upon various aerodynamic characteristics such as the lift coefficient CL, drag coefficient CD and the lift-to-drag ratio CL/CD. Besides, we attempt to visualise the flow structure in three dimension.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: The Proceedings of Mechanical Engineering Congress, Japan
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
