3/19/2023 0 Comments Flying wing airfoil![]() ![]() However, to date, neither SGE nor DGE have considered the airfoil optimization in the presence of ground. In the realm of ground effect aircraft, most studies have focused on two kinds of ground effect-the steady ground effect (SGE) wherein the flying altitude does not vary with time and the dynamic ground effect (DGE) wherein the flying altitude varies continuously with time. The aerodynamic analysis requires an additional bounday condition to simulate the effect of the ground. When flying in the proximity of the ground, the flow around an aircraft is forced to be parallel to the ground due to ground effect thus, the aerodynamics in ground effect is significantly different from that in out of ground effect in unbounded flow. Therefore, it is of interest to optimize airfoils for the wings of WIG craft for superior performnace by increasing lift as well as the lift to drag ratio. These advantages make WIG craft attractive for many military and civil applications which require take-off and landing from aircraft carriers from and to water surface, respectively. WIG craft is more fuel efficient than other general aviation and transport aircrafts and has relatively very short take-off distance. Wing in ground effect (WIG) craft is a type of aircraft which takes-off and lands with very small ground clearance compared to other transport aircrafts. The close proximity of the ground alters the flow of air around the wing causing an increase in the lift and a reduction in the induced drag of the wing. Ground effect is an aerodynamic phenomenon that occurs on an aircraft during take-off and landing when the aircraft is in close vicinity of the ground. It is demonstrated that the performance of a wing in ground (WIG) aircraft can be improved by using the optimized airfoil. The results show significant improvement in both the lift coefficient and lift to drag ratio of the optimized airfoil compared to the original NACA 4412 airfoil. The commercial software ANSYS FLUENT is employed to calculate the flow field on an adaptive structured mesh generated by ANSYS ICEM software using the Reynolds-Averaged Navier-Stokes (RANS) equations in conjunction with a one equation Spalart-Allmaras (SA) turbulence model. This paper employs a multiobjective genetic algorithm (MOGA) to optimize the shape of a widely used wing in ground (WIG) aircraft airfoil NACA 4412 to improve its lift and drag characteristics, in particular to achieve two objectives, that is, to increase its lift and its lift to drag ratio. ![]()
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