Report

6.The computer model (2/2) f. The calculation grid for the front wing was constructed to include 1764 cells. Fig. 4 shows the grid of the front wing in ground effect. Fig. 5, which has 10,968 cells, shows the grid pattern for the back wing. g. A grid independency test was performed on the front airfoil to determine a suitable mesh size for the problem. h. Three nodal densities were chosen for the runs, i.e. 2208, 4416 and 8832 nodes. Fig. 6 and Table 1 present results to validate the choice of grid density. Fig. 6 2016/7/13 1 7.Results and discussions (1/5) a. b. The results of the computer simulations were complied and plotted graphically. Front wing and rear wing Ps： the non-dimensional u/U u is the horizontal velocity near the wing . U is the frees tream horizontal velocity used at the entry to the solution field. x is the horizontal dimensional variable starting from the front tip of the wing, c is the chordal length of the wing horizontally from the upstream tip to the wing’s tail. 2016/7/13 2