Aerodynamic Analysis of Double Wedge Airfoil 16.5% @ 50% in Different Angle of Attack at Supersonic Flow

Abstract

Double wedge airfoil is one of the most efficient airfoils at supersonic speeds.these airfoils have sharp
edges and enhance the aerodynamic characteristics by oblique shock waves.In this study double
wedge airfoil 16.5% @ 50% has been studied.Numerical solution method was used for the study and
aerodynamic characteristics including lift coefficient and drag coefficient and pressure coefficient
was calculated from -15 to +15 angle of attack in Mach number equal to2.It was observed that the
lift coefficient increases for the positive attack angle by increasing the angle of attack until AOA=5
and after that reduced and for the negative attack angle the situation is the opposite positive attack
angle conditions. It was observed that as the angle of attack for positive and negative attack angle
increases, the drag coefficient always increases. It was observed that that as the angle of attack for
positive and negative attack angle increases, the value of the pressure coefficient is always reduced,
however this decrease is more severe under negative attack angle conditions. The results showed for
the angle of attack from 0 to +5 and 0 to -5, the absolute mathematical value of aerodynamic efficiency
increases with a large slope, but then decreases from 5 to 10 and from -5 to -10, the aerodynamic
efficiency decreases with a large slope and then approaches 0 with a gentle slope. Finally, the results
of the numerical solution method were compared with the experiment, which had the highest error of
about 7%, which indicates the reliability of the numerical solution results