XFOIL Version 6.96 Calculated polar for: SIKORSKY SC1094R8 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.500 -0.5374 0.08541 0.08382 -0.0047 1.0000 0.0179 -7.250 -0.5369 0.08099 0.07942 -0.0083 1.0000 0.0181 -7.000 -0.5394 0.07527 0.07371 -0.0154 1.0000 0.0182 -6.750 -0.5352 0.06935 0.06774 -0.0216 1.0000 0.0186 -6.500 -0.5290 0.06341 0.06172 -0.0265 1.0000 0.0191 -6.250 -0.5262 0.04954 0.04745 -0.0336 1.0000 0.0203 -6.000 -0.5279 0.04094 0.03854 -0.0350 1.0000 0.0206 -5.750 -0.5109 0.03906 0.03660 -0.0348 1.0000 0.0207 -5.500 -0.4943 0.03736 0.03483 -0.0341 1.0000 0.0209 -5.250 -0.4796 0.03580 0.03321 -0.0328 0.9997 0.0212 -5.000 -0.4604 0.02303 0.01935 -0.0339 0.9953 0.0199 -4.750 -0.4316 0.01902 0.01492 -0.0349 0.9918 0.0192 -4.500 -0.4004 0.01598 0.01144 -0.0355 0.9850 0.0187 -4.250 -0.3719 0.01439 0.00960 -0.0352 0.9748 0.0186 -4.000 -0.3479 0.01339 0.00844 -0.0339 0.9639 0.0187 -3.750 -0.3233 0.01271 0.00767 -0.0328 0.9547 0.0190 -3.500 -0.2987 0.01212 0.00699 -0.0316 0.9454 0.0193 -3.250 -0.2739 0.01150 0.00629 -0.0303 0.9355 0.0195 -3.000 -0.2482 0.01098 0.00570 -0.0293 0.9252 0.0198 -2.750 -0.2224 0.01060 0.00524 -0.0283 0.9151 0.0201 -2.500 -0.1968 0.01000 0.00458 -0.0273 0.9033 0.0205 -2.250 -0.1708 0.00946 0.00401 -0.0265 0.8896 0.0211 -2.000 -0.1443 0.00920 0.00370 -0.0256 0.8726 0.0218 -1.750 -0.1177 0.00898 0.00341 -0.0248 0.8521 0.0225 -1.500 -0.0905 0.00877 0.00313 -0.0241 0.8304 0.0233 -1.250 -0.0628 0.00863 0.00291 -0.0235 0.8079 0.0240 -1.000 -0.0354 0.00832 0.00251 -0.0229 0.7844 0.0253 -0.750 -0.0073 0.00820 0.00232 -0.0224 0.7586 0.0266 -0.500 0.0207 0.00815 0.00216 -0.0219 0.7271 0.0282 -0.250 0.0486 0.00806 0.00195 -0.0214 0.6867 0.0305 0.000 0.0767 0.00811 0.00183 -0.0209 0.6394 0.0329 0.250 0.1047 0.00816 0.00170 -0.0205 0.5842 0.0366 0.500 0.1327 0.00826 0.00162 -0.0202 0.5263 0.0428 0.750 0.1608 0.00828 0.00156 -0.0199 0.4749 0.0705 1.000 0.1889 0.00820 0.00154 -0.0197 0.4307 0.1400 1.250 0.2158 0.00727 0.00148 -0.0200 0.3934 0.4779 1.500 0.2419 0.00660 0.00153 -0.0196 0.3597 0.7418 1.750 0.2674 0.00651 0.00161 -0.0186 0.3306 0.8360 2.000 0.2915 0.00652 0.00170 -0.0171 0.3081 0.8927 2.250 0.3138 0.00661 0.00177 -0.0152 0.2872 0.9331 2.500 0.3357 0.00673 0.00183 -0.0132 0.2657 0.9606 2.750 0.3616 0.00683 0.00183 -0.0121 0.2421 0.9816 3.000 0.4056 0.00708 0.00190 -0.0149 0.2093 0.9974 3.250 0.4386 0.00731 0.00198 -0.0157 0.1866 1.0000 3.500 0.4634 0.00748 0.00205 -0.0147 0.1731 1.0000 3.750 0.4897 0.00764 0.00214 -0.0140 0.1623 1.0000 4.000 0.5167 0.00783 0.00224 -0.0135 0.1517 1.0000 4.250 0.5445 0.00798 0.00234 -0.0131 0.1449 1.0000 4.500 0.5723 0.00818 0.00246 -0.0127 0.1366 1.0000 4.750 0.6004 0.00833 0.00257 -0.0123 0.1310 1.0000 5.000 0.6282 0.00855 0.00272 -0.0120 0.1232 1.0000 5.250 0.6565 0.00869 0.00284 -0.0116 0.1198 1.0000 5.500 0.6845 0.00888 0.00298 -0.0113 0.1153 1.0000 5.750 0.7122 0.00914 0.00318 -0.0109 0.1096 1.0000 6.000 0.7404 0.00928 0.00332 -0.0105 0.1077 1.0000 6.250 0.7683 0.00946 0.00348 -0.0101 0.1050 1.0000 6.500 0.7961 0.00967 0.00366 -0.0097 0.1021 1.0000 6.750 0.8235 0.00996 0.00390 -0.0093 0.0984 1.0000 7.000 0.8511 0.01018 0.00413 -0.0089 0.0965 1.0000 7.250 0.8788 0.01036 0.00432 -0.0085 0.0952 1.0000 7.500 0.9064 0.01055 0.00451 -0.0081 0.0935 1.0000 7.750 0.9338 0.01077 0.00472 -0.0076 0.0916 1.0000 8.000 0.9610 0.01103 0.00496 -0.0072 0.0898 1.0000 8.250 0.9876 0.01136 0.00528 -0.0067 0.0877 1.0000 8.500 1.0136 0.01178 0.00572 -0.0061 0.0856 1.0000 8.750 1.0408 0.01199 0.00595 -0.0056 0.0850 1.0000 9.000 1.0677 0.01222 0.00620 -0.0051 0.0842 1.0000 9.250 1.0944 0.01248 0.00648 -0.0046 0.0833 1.0000 9.500 1.1209 0.01275 0.00678 -0.0041 0.0823 1.0000 9.750 1.1472 0.01304 0.00708 -0.0035 0.0813 1.0000 10.000 1.1733 0.01334 0.00740 -0.0029 0.0804 1.0000 10.250 1.1992 0.01366 0.00773 -0.0024 0.0793 1.0000 10.500 1.2246 0.01403 0.00811 -0.0017 0.0780 1.0000 10.750 1.2488 0.01455 0.00865 -0.0010 0.0766 1.0000 11.000 1.2712 0.01530 0.00945 0.0000 0.0752 1.0000 11.250 1.2966 0.01560 0.00979 0.0006 0.0749 1.0000 11.500 1.3217 0.01592 0.01016 0.0013 0.0745 1.0000 11.750 1.3464 0.01628 0.01057 0.0020 0.0740 1.0000 12.000 1.3708 0.01666 0.01100 0.0028 0.0735 1.0000 12.250 1.3948 0.01706 0.01145 0.0036 0.0729 1.0000 12.500 1.4188 0.01743 0.01187 0.0043 0.0721 1.0000 12.750 1.4427 0.01779 0.01226 0.0051 0.0713 1.0000 13.000 1.4663 0.01817 0.01267 0.0059 0.0705 1.0000 13.250 1.4897 0.01852 0.01306 0.0067 0.0696 1.0000 13.500 1.5124 0.01894 0.01349 0.0076 0.0686 1.0000 13.750 1.5330 0.01955 0.01414 0.0087 0.0675 1.0000 14.000 1.5497 0.02054 0.01519 0.0101 0.0662 1.0000 14.250 1.5685 0.02126 0.01599 0.0114 0.0657 1.0000 14.500 1.5904 0.02161 0.01640 0.0123 0.0653 1.0000 14.750 1.6120 0.02195 0.01681 0.0133 0.0648 1.0000 15.000 1.6322 0.02239 0.01732 0.0144 0.0642 1.0000 15.250 1.6518 0.02284 0.01784 0.0156 0.0634 1.0000 15.500 1.6712 0.02325 0.01829 0.0168 0.0625 1.0000 15.750 1.6889 0.02366 0.01875 0.0182 0.0616 1.0000 16.000 1.7046 0.02414 0.01926 0.0199 0.0608 1.0000 16.250 1.7183 0.02477 0.01993 0.0216 0.0598 1.0000 16.500 1.7281 0.02570 0.02092 0.0234 0.0588 1.0000 16.750 1.7307 0.02723 0.02251 0.0256 0.0576 1.0000 17.000 1.7451 0.02796 0.02333 0.0267 0.0571 1.0000 17.250 1.7596 0.02873 0.02419 0.0278 0.0566 1.0000 17.500 1.7722 0.02967 0.02522 0.0288 0.0559 1.0000 17.750 1.7844 0.03070 0.02633 0.0297 0.0551 1.0000 18.000 1.7965 0.03177 0.02747 0.0305 0.0540 1.0000 18.250 1.8072 0.03302 0.02877 0.0312 0.0529 1.0000 18.500 1.8147 0.03466 0.03045 0.0316 0.0517 1.0000 18.750 1.8152 0.03709 0.03295 0.0318 0.0505 1.0000 19.000 1.8193 0.03926 0.03523 0.0318 0.0496 1.0000 19.250 1.8273 0.04110 0.03717 0.0318 0.0485 1.0000