Research Article

Comparative Study and Aerodynamic Analysis of Rectangular Wing Using High-Lift Systems

Table 3

CFD results for wing with flap gap of 7.5 mm.

AlphaConfiguration 1 plain wingConfiguration 2 flap 10° (deg)Configuration 3 flap 20° (deg)Configuration 4 flap 30° (deg)

Mach no. 0.2 @ sea level (gap 7.5 mm)
-4°0.41530.02030.7350.05960.90550.10521.05550.1528
-2°0.44840.01920.76890.05390.93710.10221.0860.1471
0.48050.02090.79480.05390.96530.09871.11490.143
0.51150.03180.83140.07970.99380.12791.14060.1767
0.54320.04890.86120.10711.01270.16541.16460.2118
0.57040.07280.8830.13551.03210.18951.18570.248
0.59830.09740.90830.16551.04620.22631.20520.2853
10°0.62760.11960.93110.19691.06290.26161.22270.3236
12°0.65010.14330.95820.24051.07630.29641.23910.3629
14°0.66620.18170.97030.32161.07090.37751.2330.4525
16°0.66230.22510.93170.48781.01110.5811.17260.716
Mach no. 0.3 @ sea level (gap 7.5 mm)
-4°0.42130.01990.74450.05970.91940.10981.06170.1525
-2°0.45450.01880.77840.0550.94630.1051.09260.1469
0.48670.02440.81040.05390.97440.10031.12140.1427
0.51780.04010.84090.07981.00510.12821.14760.1766
0.54790.05760.86950.10741.02810.16131.17070.2116
0.57680.07670.89630.13641.04670.19121.19240.248
0.60480.09750.92140.1671.05550.22331.2120.2854
10°0.6320.11990.94530.19891.07230.26121.22980.3238
12°0.65350.14480.96780.2321.08560.29741.24210.3814
14°0.6690.18540.97540.32131.08190.3881.2390.4897
16°0.66470.23130.93820.49771.02060.60221.17930.7519
Mach no. 0.4 @ sea level (gap 7.5 mm)
-4°0.42510.01970.74970.05960.92970.11251.06660.1524
-2°0.45830.01850.78280.05430.95840.10531.09790.1468
0.48960.02390.81580.05380.98260.09091.12950.1417
0.52180.03980.84620.07981.01170.12631.15270.1765
0.5520.05740.87940.10241.04190.16491.17590.2116
0.5810.07670.91350.1351.06060.19541.19740.2479
0.6090.09760.94590.16741.0740.22571.2170.2853
10°0.63620.12010.96040.19951.09180.26941.23470.3238
12°0.6630.14410.99490.24271.10340.31171.24920.3831
14°0.68740.18381.00210.33381.09960.42161.24310.4928
16°0.68570.26080.96280.521.03740.64511.17860.7762