Open AccessMoving Surface Boundary Layer Technique For NACA 0012 Airfoil At Ultra-Low Reynolds Number
Author(s) -
Yogesh N Joshi,
Ankit Kumar,
Amrit Kumar Roy,
Atal Bihari Harichandan
Publication year - 2019
Publication title -
international journal of innovative technology and exploring engineering
Language(s) - English
Resource type - Journals
ISSN - 2278-3075
DOI - 10.35940/ijitee.b6299.129219
Subject(s) - airfoil , naca airfoil , reynolds number , chord (peer to peer) , boundary layer , leading edge , mechanics , aerodynamics , trailing edge , physics , aerospace engineering , materials science , geometry , mathematics , computer science , engineering , turbulence , distributed computing
Application of moving surface boundary layer control technique has been confined to relatively high Reynolds numbers. The present paper reports a numerical study of application of the above flow technique in the ultra-low Reynolds number range. A two dimensional incompressible unstructured grid based Navier Stokes solver has been used for conducting the numerical studies. Moving surface has been applied at three different portions on the airfoil surface, firstly, in the form of a rotating leading edge portion of the airfoil, secondly, a continuous moving surface from leading edge of airfoil to 57% of the chord along the leeward surface of the airfoil and thirdly a continuous moving surface from leading edge to 97% of the chord along the leeward surface of the airfoil. All the moving surface configurations show improvement of aerodynamic performance of the airfoil through enhancement of lift and decrement of drag as compared to a fixed surface one