XFOIL Version 6.96 Calculated polar for: SIKORSKY SC2110 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5767 0.08876 0.08661 0.0045 0.9271 0.0107 -8.500 -0.5781 0.08468 0.08253 0.0018 0.9233 0.0105 -8.250 -0.5841 0.07847 0.07630 -0.0055 0.9173 0.0103 -8.000 -0.5901 0.07322 0.07097 -0.0092 0.9120 0.0102 -7.750 -0.5917 0.06789 0.06552 -0.0120 0.9081 0.0100 -7.500 -0.5881 0.06242 0.05992 -0.0145 0.9039 0.0099 -7.250 -0.5819 0.05719 0.05451 -0.0159 0.8998 0.0098 -7.000 -0.5732 0.05222 0.04933 -0.0165 0.8962 0.0097 -6.750 -0.5622 0.04744 0.04431 -0.0165 0.8933 0.0097 -6.500 -0.5469 0.04254 0.03914 -0.0166 0.8900 0.0096 -6.250 -0.5293 0.03812 0.03443 -0.0163 0.8865 0.0099 -6.000 -0.5109 0.03350 0.02946 -0.0156 0.8832 0.0101 -5.750 -0.4917 0.02891 0.02445 -0.0146 0.8805 0.0099 -5.500 -0.4715 0.02415 0.01915 -0.0133 0.8780 0.0097 -5.250 -0.4476 0.02007 0.01452 -0.0124 0.8752 0.0097 -5.000 -0.4214 0.01766 0.01173 -0.0119 0.8721 0.0100 -4.750 -0.3947 0.01609 0.00990 -0.0115 0.8692 0.0103 -4.500 -0.3679 0.01499 0.00860 -0.0112 0.8663 0.0107 -4.250 -0.3412 0.01420 0.00767 -0.0108 0.8637 0.0110 -4.000 -0.3148 0.01349 0.00690 -0.0105 0.8613 0.0114 -3.750 -0.2864 0.01301 0.00642 -0.0106 0.8566 0.0118 -3.500 -0.2595 0.01253 0.00589 -0.0103 0.8499 0.0122 -3.250 -0.2329 0.01206 0.00536 -0.0099 0.8426 0.0128 -3.000 -0.2050 0.01168 0.00492 -0.0098 0.8349 0.0137 -2.750 -0.1780 0.01127 0.00448 -0.0095 0.8282 0.0146 -2.500 -0.1495 0.01094 0.00415 -0.0096 0.8201 0.0155 -2.250 -0.1217 0.01061 0.00377 -0.0094 0.8124 0.0165 -2.000 -0.0931 0.01032 0.00343 -0.0094 0.8028 0.0175 -1.750 -0.0647 0.01002 0.00313 -0.0095 0.7933 0.0190 -1.500 -0.0362 0.00984 0.00290 -0.0095 0.7822 0.0212 -1.250 -0.0075 0.00960 0.00264 -0.0095 0.7682 0.0236 -1.000 0.0214 0.00944 0.00242 -0.0096 0.7515 0.0264 -0.750 0.0504 0.00928 0.00221 -0.0097 0.7281 0.0321 -0.500 0.0793 0.00914 0.00203 -0.0099 0.6974 0.0462 -0.250 0.1083 0.00880 0.00186 -0.0103 0.6494 0.1575 0.000 0.1352 0.00715 0.00170 -0.0117 0.5641 0.7001 0.250 0.1622 0.00744 0.00187 -0.0116 0.4535 0.7942 0.500 0.1881 0.00778 0.00204 -0.0112 0.3779 0.8416 0.750 0.2142 0.00803 0.00215 -0.0107 0.3366 0.8693 1.000 0.2411 0.00823 0.00223 -0.0104 0.3099 0.8846 1.250 0.2688 0.00839 0.00229 -0.0104 0.2890 0.8924 1.500 0.2971 0.00856 0.00234 -0.0105 0.2695 0.9000 1.750 0.3243 0.00871 0.00241 -0.0103 0.2537 0.9074 2.000 0.3524 0.00886 0.00247 -0.0104 0.2412 0.9150 2.250 0.3790 0.00900 0.00255 -0.0100 0.2293 0.9218 2.750 0.4331 0.00928 0.00271 -0.0097 0.2071 0.9361 3.000 0.4601 0.00943 0.00280 -0.0095 0.1987 0.9437 3.250 0.4867 0.00956 0.00289 -0.0092 0.1906 0.9504 3.500 0.5136 0.00971 0.00299 -0.0090 0.1829 0.9580 3.750 0.5409 0.00985 0.00309 -0.0090 0.1747 0.9648 4.000 0.5688 0.01000 0.00320 -0.0090 0.1682 0.9725 4.250 0.5989 0.01015 0.00333 -0.0096 0.1619 0.9786 4.500 0.6294 0.01035 0.00347 -0.0103 0.1557 0.9853 4.750 0.6615 0.01051 0.00362 -0.0114 0.1497 0.9917 5.000 0.6924 0.01073 0.00379 -0.0123 0.1433 1.0000 5.250 0.7206 0.01092 0.00397 -0.0126 0.1390 1.0000 5.500 0.7487 0.01113 0.00416 -0.0129 0.1343 1.0000 5.750 0.7766 0.01139 0.00438 -0.0132 0.1290 1.0000 6.000 0.8047 0.01161 0.00460 -0.0134 0.1249 1.0000 6.250 0.8326 0.01184 0.00483 -0.0137 0.1209 1.0000 6.500 0.8603 0.01211 0.00508 -0.0139 0.1168 1.0000 6.750 0.8878 0.01239 0.00536 -0.0141 0.1134 1.0000 7.000 0.9155 0.01263 0.00563 -0.0143 0.1102 1.0000 7.250 0.9428 0.01291 0.00590 -0.0145 0.1064 1.0000 7.500 0.9698 0.01324 0.00622 -0.0147 0.1028 1.0000 7.750 0.9968 0.01354 0.00654 -0.0148 0.1002 1.0000 8.000 1.0238 0.01382 0.00687 -0.0149 0.0978 1.0000 8.250 1.0504 0.01413 0.00720 -0.0150 0.0949 1.0000 8.500 1.0767 0.01449 0.00756 -0.0151 0.0916 1.0000 8.750 1.1026 0.01488 0.00797 -0.0151 0.0888 1.0000 9.000 1.1289 0.01520 0.00835 -0.0151 0.0869 1.0000 9.250 1.1548 0.01555 0.00875 -0.0151 0.0846 1.0000 9.500 1.1803 0.01592 0.00915 -0.0151 0.0820 1.0000 9.750 1.2052 0.01637 0.00961 -0.0150 0.0792 1.0000 10.000 1.2299 0.01682 0.01010 -0.0149 0.0771 1.0000 10.250 1.2550 0.01718 0.01055 -0.0148 0.0751 1.0000 10.500 1.2796 0.01759 0.01101 -0.0147 0.0723 1.0000 10.750 1.3034 0.01806 0.01149 -0.0145 0.0693 1.0000 11.000 1.3265 0.01861 0.01207 -0.0142 0.0669 1.0000 11.250 1.3502 0.01903 0.01259 -0.0140 0.0650 1.0000 11.500 1.3733 0.01950 0.01313 -0.0137 0.0624 1.0000 11.750 1.3954 0.02006 0.01371 -0.0133 0.0596 1.0000 12.000 1.4165 0.02068 0.01438 -0.0128 0.0573 1.0000 12.250 1.4382 0.02120 0.01499 -0.0124 0.0554 1.0000 12.500 1.4588 0.02179 0.01565 -0.0119 0.0527 1.0000 12.750 1.4778 0.02250 0.01639 -0.0112 0.0498 1.0000 13.000 1.4966 0.02317 0.01714 -0.0105 0.0472 1.0000 13.250 1.5140 0.02389 0.01793 -0.0096 0.0444 1.0000 13.500 1.5274 0.02475 0.01884 -0.0083 0.0419 1.0000 13.750 1.5409 0.02562 0.01980 -0.0071 0.0398 1.0000 14.000 1.5538 0.02657 0.02083 -0.0059 0.0373 1.0000 14.250 1.5642 0.02775 0.02206 -0.0046 0.0345 1.0000 14.500 1.5744 0.02893 0.02333 -0.0034 0.0318 1.0000 14.750 1.5811 0.03045 0.02491 -0.0021 0.0285 1.0000 15.000 1.5869 0.03208 0.02662 -0.0009 0.0253 1.0000 15.250 1.5884 0.03414 0.02875 0.0003 0.0219 1.0000 15.500 1.5868 0.03659 0.03129 0.0013 0.0188 1.0000 15.750 1.5830 0.03936 0.03416 0.0020 0.0161 1.0000 16.000 1.5758 0.04269 0.03761 0.0022 0.0140 1.0000 16.250 1.5662 0.04653 0.04159 0.0019 0.0126 1.0000 16.500 1.5531 0.05120 0.04642 0.0007 0.0117 1.0000 16.750 1.5374 0.05673 0.05213 -0.0015 0.0112 1.0000 17.000 1.5160 0.06388 0.05949 -0.0052 0.0110 1.0000 17.250 1.4860 0.07345 0.06929 -0.0108 0.0112 1.0000 17.750 1.4059 0.09668 0.09301 -0.0233 0.0131 1.0000 18.000 1.3637 0.10814 0.10467 -0.0290 0.0146 1.0000