Numerical and Experimental Study on Aerodynamic Characteristic of Basic Airfoils at Low Reynolds Numbers

摘要

The aerodynamic characteristics of airfoils have been researched in higher Reynolds-number ranges more than 106, in a historic context closely related with airplanes' and fluid-machinery developments in the last century, however our knowledge is not enough at low and middle Reynolds-number ranges. So, in the present study, we investigate such basic airfoils as a NACA0015, a flat plate and the flat plates with modified fore-face and after-facegeometries in a Reynoldsnumber range of 102-105, using two- and three-dimensional computations together with wind-tunnel and water-tank experiments. Especially, we show their flow fields at Re = 1.0 x102.