Nowadays, the development of aviation technology is rapidly progressing. One of the recent developments is wing-in-ground vehicles. A wing-in-ground vehicle is an aerial vehicle that implement wing-in-ground effect. Wing-in-ground effect is a phenomenon in which lift increases while drag decreases when a wing is in a close proximity to ground. During its early years, the wing-in-ground vehicle was developed with straight wing.However, straight wings were difficult to control so that inverted delta wings were used as an alternative.This change introduced the need to simulate the wing-in-ground effect on inverted delta wing and study the resulting aerodynamic forces.
This study uses Ansys Fluent 17.2 with a grid number of about 6.6 millions and a computational domain with a length of 5 m, a width 1.125 m, and a height of 1.5 m. The wing is placed 370.79 cm from the outlet and in this study only half of the wing is simulated to speed up the calculation and reduce the number of mesh. The angle-of-attack used is 5°. In this study the velocity, flying altitude, and swept angle are varied.The simulated velocities are 12 m/s, 24 m/s, 36 m/s, and 48 m/s. The flying altitude is represented by the ratio of height to chord (h/c), the simulated h/c is 0.1344, 0.2688, and 0.4032. The swept angles to be simulated include: 45°, 60°, 74.98°, and 85°.From the comparison made, it can be seen that the speed of 48 m/s has a value of CL and CD higher than at 12 m/s, 24 m/s, and 36 m/s. In addition, h/c = 0.1344 has higher values of CL and CDthan h/c = 0.2488 and h/c = 0.4032. The simulation results also show that 45° sweep angle generates the highest CLand CD values. |