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

Year 2018, Volume: 4 Issue: 4, 153 - 160, 19.02.2019

Haci Sogukpinar

Abstract

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.

Keywords

3D simulation, Aircraft, vortex, airfoil, Aerodynamic Analysis, lift, drag

References

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