XFOIL Version 6.94 Calculated polar for: gradus3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.010 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1221 0.04749 0.03058 -0.0230 0.9999 1.0001 -2.500 -0.0936 0.04647 0.02828 -0.0232 0.9999 1.0001 -2.000 -0.0510 0.04650 0.02712 -0.0237 0.9999 1.0001 -1.500 -0.0047 0.04695 0.02662 -0.0241 0.9999 1.0001 -1.000 0.0423 0.04767 0.02661 -0.0243 0.9999 1.0001 -0.500 0.0888 0.04859 0.02690 -0.0243 0.9999 1.0001 0.000 0.1340 0.04971 0.02770 -0.0241 0.9999 1.0001 0.500 0.1768 0.05110 0.02898 -0.0239 0.9999 1.0001 1.000 0.2147 0.05299 0.03102 -0.0236 0.9999 1.0001 1.500 0.2373 0.05638 0.03484 -0.0236 0.9999 1.0001 2.000 0.2165 0.06431 0.04306 -0.0252 0.9999 1.0001 2.500 0.2128 0.07131 0.04991 -0.0277 0.9999 1.0001 3.000 0.2234 0.07714 0.05550 -0.0298 0.9999 1.0001 3.500 0.2392 0.08257 0.06068 -0.0316 0.9999 1.0001 4.000 0.2576 0.08785 0.06572 -0.0333 0.9999 1.0001 4.500 0.2772 0.09307 0.07072 -0.0348 0.9999 1.0001 5.000 0.2976 0.09828 0.07573 -0.0363 0.9999 1.0001