XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1012R8 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4627 0.08605 0.08375 -0.0206 1.0000 0.0302 -8.750 -0.4618 0.08197 0.07970 -0.0223 1.0000 0.0304 -8.500 -0.4589 0.07833 0.07609 -0.0246 1.0000 0.0305 -8.250 -0.4622 0.07363 0.07138 -0.0292 1.0000 0.0306 -8.000 -0.4605 0.07009 0.06783 -0.0312 1.0000 0.0308 -7.750 -0.4568 0.06667 0.06438 -0.0329 1.0000 0.0310 -7.500 -0.4555 0.06346 0.06115 -0.0336 1.0000 0.0313 -7.250 -0.4645 0.06104 0.05869 -0.0314 1.0000 0.0315 -7.000 -0.4659 0.04812 0.04503 -0.0385 0.9939 0.0347 -6.750 -0.4391 0.04553 0.04248 -0.0407 0.9904 0.0350 -6.500 -0.4076 0.04326 0.04017 -0.0435 0.9869 0.0353 -6.250 -0.3755 0.04094 0.03778 -0.0463 0.9811 0.0358 -6.000 -0.3482 0.03852 0.03524 -0.0478 0.9731 0.0367 -5.750 -0.3481 0.02445 0.01953 -0.0451 0.9613 0.0306 -5.500 -0.3265 0.02292 0.01796 -0.0438 0.9506 0.0295 -5.250 -0.3063 0.02038 0.01511 -0.0422 0.9407 0.0286 -5.000 -0.2844 0.01827 0.01266 -0.0406 0.9321 0.0283 -4.750 -0.2611 0.01697 0.01115 -0.0392 0.9227 0.0284 -4.500 -0.2363 0.01595 0.00997 -0.0382 0.9132 0.0288 -4.250 -0.2118 0.01511 0.00898 -0.0370 0.9044 0.0292 -4.000 -0.1856 0.01440 0.00815 -0.0362 0.8935 0.0297 -3.750 -0.1598 0.01390 0.00751 -0.0352 0.8834 0.0302 -3.500 -0.1341 0.01304 0.00667 -0.0345 0.8721 0.0311 -3.250 -0.1076 0.01267 0.00629 -0.0338 0.8597 0.0322 -3.000 -0.0813 0.01230 0.00586 -0.0330 0.8443 0.0333 -2.750 -0.0547 0.01195 0.00541 -0.0322 0.8264 0.0343 -2.500 -0.0285 0.01141 0.00483 -0.0315 0.8075 0.0354 -2.250 -0.0014 0.01110 0.00450 -0.0310 0.7880 0.0367 -2.000 0.0261 0.01086 0.00418 -0.0305 0.7671 0.0383 -1.750 0.0535 0.01058 0.00384 -0.0301 0.7434 0.0404 -1.500 0.0811 0.01043 0.00361 -0.0297 0.7160 0.0429 -1.250 0.1088 0.01026 0.00333 -0.0293 0.6833 0.0456 -1.000 0.1365 0.01018 0.00313 -0.0290 0.6456 0.0494 -0.750 0.1641 0.01013 0.00295 -0.0287 0.6041 0.0558 -0.500 0.1916 0.01007 0.00279 -0.0285 0.5577 0.0718 -0.250 0.2189 0.00999 0.00270 -0.0283 0.5109 0.1216 0.000 0.2451 0.00941 0.00260 -0.0285 0.4693 0.3186 0.250 0.2665 0.00816 0.00265 -0.0277 0.4350 0.7404 0.500 0.2897 0.00814 0.00279 -0.0262 0.4047 0.8323 0.750 0.3125 0.00827 0.00291 -0.0245 0.3792 0.8793 1.000 0.3337 0.00843 0.00303 -0.0224 0.3575 0.9147 1.250 0.3534 0.00861 0.00313 -0.0199 0.3389 0.9440 1.500 0.3760 0.00875 0.00318 -0.0182 0.3208 0.9680 1.750 0.4121 0.00894 0.00323 -0.0195 0.2994 0.9825 2.000 0.4617 0.00926 0.00335 -0.0239 0.2728 0.9904 2.250 0.5096 0.00955 0.00347 -0.0279 0.2464 0.9960 2.500 0.5500 0.00984 0.00357 -0.0306 0.2222 0.9996 2.750 0.5739 0.01004 0.00364 -0.0300 0.2062 1.0000 3.000 0.5959 0.01023 0.00374 -0.0289 0.1942 1.0000 3.250 0.6179 0.01045 0.00386 -0.0278 0.1842 1.0000 3.500 0.6402 0.01066 0.00399 -0.0267 0.1756 1.0000 3.750 0.6631 0.01089 0.00415 -0.0257 0.1685 1.0000 4.000 0.6870 0.01111 0.00430 -0.0249 0.1622 1.0000 4.250 0.7115 0.01143 0.00453 -0.0243 0.1559 1.0000 4.500 0.7379 0.01161 0.00471 -0.0240 0.1515 1.0000 4.750 0.7641 0.01188 0.00491 -0.0237 0.1466 1.0000 5.000 0.7899 0.01225 0.00521 -0.0233 0.1416 1.0000 5.250 0.8172 0.01245 0.00541 -0.0232 0.1383 1.0000 5.500 0.8441 0.01270 0.00562 -0.0230 0.1345 1.0000 5.750 0.8701 0.01307 0.00593 -0.0228 0.1306 1.0000 6.000 0.8964 0.01342 0.00627 -0.0225 0.1276 1.0000 6.250 0.9233 0.01367 0.00652 -0.0224 0.1252 1.0000 6.500 0.9500 0.01395 0.00679 -0.0222 0.1227 1.0000 6.750 0.9760 0.01429 0.00710 -0.0219 0.1202 1.0000 7.000 1.0008 0.01479 0.00755 -0.0216 0.1175 1.0000 7.250 1.0260 0.01522 0.00798 -0.0212 0.1157 1.0000 7.500 1.0522 0.01551 0.00830 -0.0210 0.1142 1.0000 7.750 1.0781 0.01583 0.00863 -0.0207 0.1124 1.0000 8.000 1.1036 0.01616 0.00897 -0.0204 0.1106 1.0000 8.250 1.1286 0.01654 0.00935 -0.0201 0.1090 1.0000 8.500 1.1527 0.01702 0.00980 -0.0196 0.1074 1.0000 8.750 1.1747 0.01775 0.01051 -0.0189 0.1055 1.0000 9.000 1.1984 0.01825 0.01104 -0.0184 0.1045 1.0000 9.250 1.2228 0.01864 0.01148 -0.0180 0.1036 1.0000 9.500 1.2466 0.01906 0.01195 -0.0175 0.1026 1.0000 9.750 1.2699 0.01952 0.01244 -0.0170 0.1015 1.0000 10.000 1.2928 0.02000 0.01296 -0.0164 0.1005 1.0000 10.250 1.3152 0.02050 0.01349 -0.0158 0.0995 1.0000 10.500 1.3370 0.02102 0.01404 -0.0151 0.0986 1.0000 10.750 1.3582 0.02159 0.01462 -0.0144 0.0977 1.0000 11.000 1.3784 0.02224 0.01527 -0.0135 0.0967 1.0000 11.250 1.3971 0.02311 0.01615 -0.0126 0.0956 1.0000 11.500 1.4152 0.02418 0.01726 -0.0116 0.0945 1.0000 11.750 1.4345 0.02474 0.01789 -0.0106 0.0941 1.0000 12.000 1.4526 0.02536 0.01859 -0.0095 0.0935 1.0000 12.250 1.4682 0.02603 0.01934 -0.0081 0.0930 1.0000 12.500 1.4832 0.02677 0.02016 -0.0066 0.0924 1.0000 12.750 1.4977 0.02757 0.02103 -0.0052 0.0918 1.0000 13.000 1.5117 0.02843 0.02196 -0.0039 0.0912 1.0000 13.250 1.5251 0.02933 0.02294 -0.0026 0.0907 1.0000 13.500 1.5380 0.03029 0.02398 -0.0013 0.0901 1.0000 13.750 1.5503 0.03131 0.02507 -0.0001 0.0896 1.0000 14.000 1.5620 0.03239 0.02622 0.0011 0.0891 1.0000 14.250 1.5733 0.03353 0.02742 0.0021 0.0886 1.0000 14.500 1.5840 0.03475 0.02870 0.0031 0.0882 1.0000 14.750 1.5942 0.03604 0.03005 0.0041 0.0877 1.0000 15.000 1.6039 0.03742 0.03150 0.0049 0.0873 1.0000 15.250 1.6129 0.03892 0.03305 0.0058 0.0868 1.0000 15.500 1.6207 0.04064 0.03483 0.0066 0.0862 1.0000 15.750 1.6248 0.04299 0.03728 0.0075 0.0855 1.0000 16.000 1.6255 0.04541 0.03984 0.0082 0.0851 1.0000 16.250 1.6267 0.04761 0.04218 0.0085 0.0849 1.0000 16.500 1.6263 0.05007 0.04477 0.0087 0.0847 1.0000 16.750 1.6240 0.05283 0.04767 0.0086 0.0844 1.0000 17.000 1.6196 0.05594 0.05094 0.0082 0.0842 1.0000 17.250 1.6127 0.05946 0.05461 0.0075 0.0839 1.0000 17.500 1.6030 0.06347 0.05878 0.0063 0.0837 1.0000 17.750 1.5897 0.06813 0.06361 0.0047 0.0834 1.0000