Low Speed Numerical Aerodynamic Analysis of New Designed 3D Transport Aircraft

In this study a new airfoil is designed by using aerodynamic features of the NACA 0012 airfoil and numerical calculation is conducted by using Spalart–Allmaras Turbulence Model and calculated lift and drag coefficients are compare with experimental result to correlate numerical calculation accuracy of CDF model. Then, according to the new airfoil data, a three dimensional aircraft fuselage, and its wings are designed and, tail section is designed by using NACA 0012 airfoil. Finally, 3D model aircraft are simulated for cruise flight, climb and descent at the angle of attack +10 and -10 degrees respectively. The simulation results are interpreted in terms of fluid dynamics. It is observed that during the ascension and descent of the aircraft, very large vortices are formed by the low pressure effect occurring at the rear upper or lower part of the fuselage. Vortexes originating from the rear body are given with the wing tip vortexes in the same figures but the vortex due to the back of the fuselage is found to be very large compared to the wingtip. Furthermore, for each simulation, the formation of the wingtip vortexes are investigated and presented. It is observed that during ascending the vortex formation is formed in roll up and roll down in the phase of descending.