XFOIL Version 6.96 Calculated polar for: RAE 100 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.7759 0.08501 0.07745 -0.0146 1.0000 0.0610 -11.000 -0.7996 0.07737 0.06975 -0.0199 1.0000 0.0606 -10.750 -0.8237 0.07108 0.06335 -0.0236 1.0000 0.0602 -10.500 -0.8482 0.06597 0.05808 -0.0250 1.0000 0.0601 -10.250 -0.8691 0.06161 0.05350 -0.0245 1.0000 0.0603 -10.000 -0.8835 0.05722 0.04874 -0.0237 1.0000 0.0608 -9.750 -0.8870 0.05335 0.04451 -0.0228 1.0000 0.0616 -9.500 -0.8783 0.05065 0.04171 -0.0219 1.0000 0.0632 -9.250 -0.8693 0.04823 0.03912 -0.0209 1.0000 0.0659 -9.000 -0.8610 0.04542 0.03597 -0.0198 1.0000 0.0690 -8.750 -0.8515 0.04233 0.03232 -0.0185 1.0000 0.0720 -8.500 -0.8354 0.03993 0.02978 -0.0176 1.0000 0.0750 -8.250 -0.8184 0.03814 0.02787 -0.0166 1.0000 0.0797 -8.000 -0.8008 0.03594 0.02515 -0.0155 1.0000 0.0853 -7.750 -0.7811 0.03426 0.02357 -0.0146 1.0000 0.0903 -7.500 -0.7612 0.03260 0.02157 -0.0136 1.0000 0.0982 -7.250 -0.7412 0.03114 0.02019 -0.0127 1.0000 0.1057 -7.000 -0.7207 0.02971 0.01864 -0.0116 1.0000 0.1157 -6.750 -0.7000 0.02840 0.01723 -0.0106 1.0000 0.1277 -6.500 -0.6797 0.02719 0.01602 -0.0096 1.0000 0.1422 -6.250 -0.6597 0.02603 0.01492 -0.0085 1.0000 0.1592 -6.000 -0.6394 0.02496 0.01386 -0.0074 1.0000 0.1812 -5.750 -0.6193 0.02394 0.01295 -0.0063 1.0000 0.2066 -5.500 -0.5991 0.02301 0.01213 -0.0052 1.0000 0.2370 -5.250 -0.5786 0.02219 0.01141 -0.0041 1.0000 0.2723 -5.000 -0.5583 0.02145 0.01081 -0.0029 1.0000 0.3095 -4.750 -0.5376 0.02082 0.01027 -0.0016 1.0000 0.3493 -4.500 -0.5170 0.02026 0.00985 -0.0002 1.0000 0.3885 -4.250 -0.4960 0.01977 0.00946 0.0012 1.0000 0.4286 -4.000 -0.4753 0.01933 0.00912 0.0027 1.0000 0.4669 -3.750 -0.4548 0.01895 0.00882 0.0044 1.0000 0.5050 -3.500 -0.4343 0.01860 0.00858 0.0062 1.0000 0.5410 -3.250 -0.4138 0.01829 0.00835 0.0080 1.0000 0.5770 -3.000 -0.3932 0.01800 0.00812 0.0098 1.0000 0.6126 -2.750 -0.3726 0.01774 0.00796 0.0117 1.0000 0.6467 -2.500 -0.3518 0.01751 0.00782 0.0136 1.0000 0.6808 -2.250 -0.3308 0.01731 0.00769 0.0155 1.0000 0.7149 -2.000 -0.3092 0.01714 0.00760 0.0173 1.0000 0.7494 -1.750 -0.2865 0.01701 0.00753 0.0189 1.0000 0.7849 -1.500 -0.2597 0.01694 0.00753 0.0197 1.0000 0.8199 -1.250 -0.2271 0.01693 0.00754 0.0193 1.0000 0.8557 -1.000 -0.1876 0.01696 0.00757 0.0173 1.0000 0.8908 -0.750 -0.1417 0.01702 0.00759 0.0138 1.0000 0.9236 -0.500 -0.0900 0.01706 0.00759 0.0089 1.0000 0.9527 -0.250 -0.0362 0.01704 0.00756 0.0031 1.0000 0.9798 0.000 0.0000 0.01700 0.00752 0.0000 1.0000 1.0000 0.250 0.0362 0.01704 0.00756 -0.0031 0.9798 1.0000 0.500 0.0900 0.01706 0.00759 -0.0089 0.9527 1.0000 0.750 0.1416 0.01702 0.00759 -0.0138 0.9236 1.0000 1.000 0.1877 0.01696 0.00757 -0.0173 0.8908 1.0000 1.250 0.2271 0.01692 0.00754 -0.0193 0.8557 1.0000 1.500 0.2597 0.01694 0.00753 -0.0197 0.8200 1.0000 1.750 0.2866 0.01701 0.00753 -0.0189 0.7850 1.0000 2.000 0.3093 0.01714 0.00760 -0.0173 0.7496 1.0000 2.250 0.3308 0.01731 0.00769 -0.0155 0.7149 1.0000 2.500 0.3518 0.01751 0.00782 -0.0137 0.6808 1.0000 2.750 0.3726 0.01774 0.00796 -0.0117 0.6467 1.0000 3.000 0.3933 0.01800 0.00812 -0.0098 0.6126 1.0000 3.250 0.4138 0.01829 0.00835 -0.0080 0.5769 1.0000 3.500 0.4344 0.01860 0.00858 -0.0062 0.5410 1.0000 3.750 0.4549 0.01895 0.00882 -0.0044 0.5050 1.0000 4.000 0.4754 0.01933 0.00912 -0.0028 0.4669 1.0000 4.250 0.4961 0.01977 0.00946 -0.0012 0.4285 1.0000 4.500 0.5171 0.02026 0.00985 0.0002 0.3885 1.0000 4.750 0.5377 0.02082 0.01027 0.0016 0.3494 1.0000 5.000 0.5584 0.02145 0.01081 0.0029 0.3095 1.0000 5.250 0.5787 0.02219 0.01141 0.0041 0.2723 1.0000 5.500 0.5991 0.02301 0.01213 0.0052 0.2370 1.0000 5.750 0.6193 0.02394 0.01295 0.0063 0.2066 1.0000 6.000 0.6394 0.02495 0.01386 0.0074 0.1812 1.0000 6.250 0.6596 0.02603 0.01492 0.0085 0.1592 1.0000 6.500 0.6797 0.02719 0.01603 0.0096 0.1423 1.0000 6.750 0.6999 0.02840 0.01723 0.0106 0.1277 1.0000 7.000 0.7206 0.02971 0.01864 0.0117 0.1158 1.0000 7.250 0.7411 0.03114 0.02019 0.0127 0.1057 1.0000 7.500 0.7610 0.03260 0.02156 0.0136 0.0983 1.0000 7.750 0.7810 0.03426 0.02356 0.0147 0.0903 1.0000 8.000 0.8007 0.03594 0.02515 0.0155 0.0852 1.0000 8.250 0.8182 0.03812 0.02785 0.0167 0.0797 1.0000 8.500 0.8353 0.03991 0.02977 0.0176 0.0750 1.0000 8.750 0.8514 0.04230 0.03229 0.0185 0.0720 1.0000 9.000 0.8609 0.04540 0.03595 0.0198 0.0690 1.0000 9.250 0.8691 0.04820 0.03910 0.0209 0.0659 1.0000 9.500 0.8781 0.05064 0.04171 0.0219 0.0633 1.0000 9.750 0.8869 0.05332 0.04449 0.0228 0.0616 1.0000 10.000 0.8834 0.05720 0.04871 0.0238 0.0608 1.0000 10.250 0.8689 0.06160 0.05349 0.0245 0.0603 1.0000 10.500 0.8494 0.06587 0.05797 0.0251 0.0602 1.0000 10.750 0.8243 0.07100 0.06327 0.0237 0.0603 1.0000 11.000 0.7997 0.07737 0.06974 0.0199 0.0606 1.0000 11.250 0.7767 0.08490 0.07733 0.0147 0.0610 1.0000