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

Table 4

CFD results for wing with flap gap of 15 mm.

Mach no. 0.4 @ sea level (gap 15 mm)
Alpha	Configuration 1 flap 10° (deg)		Configuration 2 flap 20° (deg)		Configuration 3 flap 30° (deg)
	-4°	0.6505	0.0561	0.7028	0.0985	0.7805	0.1364
0°	0.7067	0.0512	0.7543	0.0938	0.8283	0.1421
4°	0.7495	0.0982	0.7950	0.1426	0.8694	0.1845
8°	0.7825	0.1486	0.8387	0.1971	0.9042	0.2422
12°	0.8148	0.2322	0.8793	0.2770	0.9337	0.3234
16°	0.7716	0.5017	0.8253	0.5484	0.8775	0.6056