XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1095 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.8995 0.09211 0.08835 0.0071 1.0000 0.0109 -12.750 -0.9640 0.07418 0.07030 -0.0040 1.0000 0.0102 -12.500 -1.0317 0.05185 0.04747 -0.0236 1.0000 0.0095 -12.250 -1.0509 0.04585 0.04120 -0.0274 1.0000 0.0095 -12.000 -1.0621 0.04221 0.03734 -0.0274 1.0000 0.0096 -11.750 -1.0648 0.03937 0.03427 -0.0265 1.0000 0.0097 -11.500 -1.0606 0.03687 0.03154 -0.0258 1.0000 0.0099 -11.250 -1.0522 0.03463 0.02908 -0.0250 1.0000 0.0102 -11.000 -1.0406 0.03262 0.02681 -0.0242 1.0000 0.0105 -10.750 -1.0266 0.03077 0.02473 -0.0234 1.0000 0.0109 -10.500 -1.0106 0.02908 0.02279 -0.0226 1.0000 0.0115 -10.250 -0.9932 0.02748 0.02101 -0.0220 1.0000 0.0122 -10.000 -0.9739 0.02608 0.01946 -0.0214 1.0000 0.0132 -9.750 -0.9535 0.02478 0.01797 -0.0208 1.0000 0.0149 -9.500 -0.9320 0.02362 0.01671 -0.0204 1.0000 0.0173 -9.250 -0.9093 0.02262 0.01558 -0.0199 1.0000 0.0208 -9.000 -0.8855 0.02181 0.01460 -0.0195 1.0000 0.0247 -8.750 -0.8617 0.02104 0.01375 -0.0192 1.0000 0.0283 -8.500 -0.8373 0.02035 0.01295 -0.0189 1.0000 0.0321 -8.250 -0.8124 0.01980 0.01233 -0.0187 1.0000 0.0367 -8.000 -0.7876 0.01918 0.01164 -0.0184 1.0000 0.0404 -7.750 -0.7623 0.01872 0.01112 -0.0182 1.0000 0.0445 -7.500 -0.7369 0.01820 0.01052 -0.0179 1.0000 0.0486 -7.250 -0.7113 0.01779 0.01010 -0.0176 1.0000 0.0529 -7.000 -0.6855 0.01736 0.00953 -0.0173 1.0000 0.0575 -6.750 -0.6603 0.01686 0.00906 -0.0170 1.0000 0.0618 -6.500 -0.6347 0.01641 0.00854 -0.0166 1.0000 0.0666 -6.250 -0.6094 0.01593 0.00800 -0.0162 1.0000 0.0712 -6.000 -0.5839 0.01559 0.00763 -0.0158 1.0000 0.0769 -5.750 -0.5585 0.01526 0.00721 -0.0153 1.0000 0.0824 -5.500 -0.5338 0.01488 0.00685 -0.0148 1.0000 0.0877 -5.250 -0.5091 0.01459 0.00649 -0.0142 1.0000 0.0928 -5.000 -0.4851 0.01424 0.00611 -0.0135 1.0000 0.0973 -4.750 -0.4615 0.01393 0.00582 -0.0128 1.0000 0.1025 -4.500 -0.4378 0.01369 0.00553 -0.0120 1.0000 0.1078 -4.250 -0.4147 0.01338 0.00525 -0.0113 1.0000 0.1135 -4.000 -0.3914 0.01315 0.00502 -0.0105 1.0000 0.1203 -3.750 -0.3683 0.01291 0.00479 -0.0097 1.0000 0.1269 -3.500 -0.3352 0.01262 0.00453 -0.0110 0.9962 0.1346 -3.250 -0.2990 0.01233 0.00425 -0.0128 0.9913 0.1425 -3.000 -0.2622 0.01206 0.00402 -0.0148 0.9861 0.1536 -2.750 -0.2249 0.01175 0.00380 -0.0169 0.9806 0.1714 -2.500 -0.1868 0.01139 0.00360 -0.0191 0.9727 0.2027 -2.250 -0.1503 0.01099 0.00341 -0.0210 0.9600 0.2519 -2.000 -0.1188 0.01057 0.00325 -0.0217 0.9454 0.3162 -1.750 -0.0905 0.01013 0.00312 -0.0218 0.9323 0.3957 -1.500 -0.0640 0.00963 0.00303 -0.0215 0.9194 0.4956 -1.250 -0.0388 0.00917 0.00301 -0.0207 0.9062 0.6007 -1.000 -0.0143 0.00888 0.00302 -0.0194 0.8920 0.6849 -0.750 0.0099 0.00871 0.00303 -0.0179 0.8769 0.7437 -0.500 0.0336 0.00861 0.00305 -0.0163 0.8604 0.7914 -0.250 0.0569 0.00856 0.00305 -0.0145 0.8419 0.8309 0.000 0.0798 0.00854 0.00303 -0.0125 0.8154 0.8648 0.250 0.1024 0.00857 0.00300 -0.0103 0.7813 0.9035 0.500 0.1291 0.00865 0.00297 -0.0090 0.7426 0.9398 0.750 0.1616 0.00875 0.00292 -0.0093 0.7013 0.9661 1.000 0.2000 0.00892 0.00285 -0.0111 0.6467 0.9809 1.250 0.2390 0.00918 0.00281 -0.0133 0.5832 0.9915 1.500 0.2769 0.00951 0.00280 -0.0154 0.5164 0.9992 1.750 0.3017 0.00980 0.00282 -0.0150 0.4624 1.0000 2.000 0.3254 0.01010 0.00288 -0.0143 0.4159 1.0000 2.250 0.3492 0.01038 0.00296 -0.0137 0.3766 1.0000 2.500 0.3732 0.01066 0.00306 -0.0131 0.3422 1.0000 2.750 0.3976 0.01093 0.00318 -0.0125 0.3117 1.0000 3.000 0.4225 0.01122 0.00333 -0.0121 0.2826 1.0000 3.250 0.4477 0.01151 0.00349 -0.0117 0.2548 1.0000 3.500 0.4733 0.01182 0.00366 -0.0113 0.2297 1.0000 3.750 0.4991 0.01213 0.00388 -0.0110 0.2067 1.0000 4.000 0.5249 0.01248 0.00411 -0.0108 0.1871 1.0000 4.250 0.5509 0.01282 0.00436 -0.0106 0.1712 1.0000 4.750 0.6033 0.01349 0.00496 -0.0101 0.1486 1.0000 5.000 0.6294 0.01386 0.00530 -0.0099 0.1407 1.0000 5.250 0.6557 0.01421 0.00566 -0.0097 0.1332 1.0000 5.500 0.6817 0.01461 0.00603 -0.0095 0.1268 1.0000 5.750 0.7080 0.01496 0.00642 -0.0092 0.1205 1.0000 6.000 0.7335 0.01544 0.00684 -0.0090 0.1152 1.0000 6.250 0.7597 0.01582 0.00730 -0.0088 0.1111 1.0000 6.500 0.7856 0.01624 0.00777 -0.0085 0.1071 1.0000 6.750 0.8109 0.01674 0.00826 -0.0082 0.1035 1.0000 7.000 0.8360 0.01730 0.00884 -0.0079 0.1005 1.0000 7.250 0.8617 0.01775 0.00941 -0.0076 0.0973 1.0000 7.500 0.8870 0.01823 0.00996 -0.0073 0.0940 1.0000 7.750 0.9120 0.01877 0.01054 -0.0070 0.0913 1.0000 8.000 0.9361 0.01947 0.01125 -0.0065 0.0889 1.0000 8.250 0.9606 0.02014 0.01202 -0.0061 0.0870 1.0000 8.500 0.9853 0.02074 0.01277 -0.0057 0.0849 1.0000 8.750 1.0098 0.02129 0.01344 -0.0054 0.0820 1.0000 9.000 1.0341 0.02172 0.01393 -0.0051 0.0784 1.0000 9.250 1.0576 0.02220 0.01449 -0.0047 0.0740 1.0000 9.500 1.0829 0.02233 0.01477 -0.0045 0.0679 1.0000 9.750 1.1063 0.02276 0.01522 -0.0042 0.0631 1.0000 10.000 1.1307 0.02316 0.01579 -0.0039 0.0579 1.0000 10.250 1.1536 0.02367 0.01635 -0.0035 0.0532 1.0000 10.500 1.1768 0.02422 0.01710 -0.0030 0.0476 1.0000 10.750 1.1988 0.02489 0.01784 -0.0025 0.0393 1.0000 11.000 1.2175 0.02598 0.01889 -0.0018 0.0273 1.0000 11.250 1.2319 0.02761 0.02053 -0.0007 0.0200 1.0000 11.500 1.2445 0.02933 0.02237 0.0005 0.0168 1.0000 11.750 1.2559 0.03103 0.02423 0.0018 0.0150 1.0000 12.000 1.2634 0.03299 0.02635 0.0033 0.0138 1.0000 12.250 1.2710 0.03470 0.02828 0.0048 0.0130 1.0000 12.500 1.2723 0.03658 0.03036 0.0069 0.0125 1.0000 12.750 1.2706 0.03881 0.03279 0.0085 0.0121 1.0000 13.000 1.2661 0.04154 0.03571 0.0094 0.0118 1.0000 13.250 1.2584 0.04495 0.03933 0.0093 0.0116 1.0000 13.500 1.2470 0.04938 0.04397 0.0077 0.0114 1.0000 13.750 1.2313 0.05531 0.05014 0.0042 0.0114 1.0000 14.000 1.2090 0.06358 0.05866 -0.0018 0.0114 1.0000 14.250 1.1757 0.07510 0.07046 -0.0098 0.0117 1.0000 14.500 1.1275 0.08953 0.08513 -0.0185 0.0123 1.0000 14.750 1.0758 0.10421 0.09995 -0.0263 0.0132 1.0000