Study and Analytical Work Analysis on Aerodynamic Investigation of Flow Field over Airfoil in Subsonic Wind Tunnel

Abstract

Aerodynamic analysis of a low Reynolds
number airfoil is critical for numerous
applications in the fields of aerodynamics and
aeronautics, both basic and industrial. In a
subsonic wind tunnel, an experimental
evaluation was conducted over a symmetrical
airfoil NACA 0014. The studies on the airfoil

were carried out in an open circuit, suction-
type subsonic wind tunnel. Because Reynolds

number and angle of attack are two critical
parameters in the performance of an airfoil,
all experiments were carried out on an airfoil
with the angle of attack varied at four
different Reynolds numbers. The angle of
attack and Reynolds number were adjusted
from m 0o to 18o with 3o steps and 1.49x105
to

2.98x105
respectively. In this experimental
investigation, the pressure distributions over
the bottom and top surfaces of the airfoil
were acquired, as well as the coefficients of
lift and drag. At high Reynolds numbers,
maximum coefficients of lift and drag of 1.53
and 0.18 respectively are attained. The stall
condition was virtually achieved at a 15o-16o
angle of attack.