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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4550 0.08589 0.08428 -0.0115 1.0000 0.0206 -8.500 -0.4551 0.08110 0.07951 -0.0152 1.0000 0.0209 -8.250 -0.6020 0.03405 0.03119 -0.0419 0.9944 0.0197 -8.000 -0.5764 0.03241 0.02946 -0.0431 0.9895 0.0199 -7.750 -0.5693 0.02448 0.02081 -0.0433 0.9817 0.0184 -7.500 -0.5536 0.02087 0.01669 -0.0421 0.9735 0.0185 -7.250 -0.5347 0.01915 0.01469 -0.0406 0.9646 0.0186 -7.000 -0.5149 0.01777 0.01309 -0.0389 0.9551 0.0187 -6.750 -0.4942 0.01673 0.01187 -0.0373 0.9440 0.0189 -6.500 -0.4725 0.01594 0.01092 -0.0357 0.9320 0.0191 -6.250 -0.4489 0.01532 0.01016 -0.0345 0.9209 0.0193 -6.000 -0.4224 0.01487 0.00961 -0.0339 0.9116 0.0194 -5.750 -0.3989 0.01346 0.00807 -0.0330 0.9033 0.0199 -5.500 -0.3721 0.01292 0.00750 -0.0326 0.8936 0.0202 -5.250 -0.3456 0.01252 0.00706 -0.0321 0.8847 0.0205 -5.000 -0.3180 0.01214 0.00665 -0.0317 0.8753 0.0209 -4.750 -0.2908 0.01178 0.00623 -0.0313 0.8654 0.0213 -4.500 -0.2631 0.01142 0.00582 -0.0309 0.8545 0.0217 -4.250 -0.2354 0.01108 0.00543 -0.0306 0.8443 0.0221 -4.000 -0.2073 0.01082 0.00511 -0.0303 0.8329 0.0225 -3.750 -0.1800 0.01036 0.00458 -0.0299 0.8181 0.0231 -3.500 -0.1525 0.01000 0.00418 -0.0296 0.8002 0.0237 -3.250 -0.1244 0.00980 0.00392 -0.0293 0.7812 0.0244 -3.000 -0.0962 0.00963 0.00367 -0.0291 0.7585 0.0252 -2.750 -0.0678 0.00950 0.00345 -0.0289 0.7355 0.0260 -2.500 -0.0395 0.00927 0.00313 -0.0287 0.7106 0.0270 -2.250 -0.0111 0.00916 0.00294 -0.0286 0.6804 0.0282 -2.000 0.0175 0.00912 0.00278 -0.0284 0.6457 0.0294 -1.750 0.0460 0.00911 0.00262 -0.0283 0.6063 0.0304 -1.500 0.0743 0.00907 0.00244 -0.0283 0.5657 0.0321 -1.250 0.1029 0.00914 0.00236 -0.0282 0.5202 0.0339 -1.000 0.1313 0.00920 0.00226 -0.0282 0.4760 0.0365 -0.500 0.1885 0.00931 0.00214 -0.0282 0.4032 0.0466 -0.250 0.2171 0.00929 0.00210 -0.0282 0.3756 0.0670 0.000 0.2458 0.00923 0.00209 -0.0283 0.3523 0.1026 0.250 0.2745 0.00915 0.00208 -0.0284 0.3333 0.1537 0.500 0.3017 0.00824 0.00202 -0.0289 0.3166 0.4578 0.750 0.3286 0.00758 0.00206 -0.0289 0.3001 0.6989 1.000 0.3555 0.00745 0.00215 -0.0285 0.2833 0.7942 1.250 0.3821 0.00747 0.00225 -0.0279 0.2665 0.8451 1.500 0.4081 0.00756 0.00234 -0.0271 0.2491 0.8811 1.750 0.4330 0.00769 0.00245 -0.0261 0.2307 0.9092 2.000 0.4568 0.00787 0.00257 -0.0248 0.2126 0.9306 2.250 0.4794 0.00806 0.00269 -0.0233 0.1973 0.9500 2.500 0.4997 0.00819 0.00275 -0.0212 0.1849 0.9680 2.750 0.5254 0.00832 0.00280 -0.0204 0.1741 0.9815 3.000 0.5602 0.00847 0.00290 -0.0217 0.1655 0.9888 3.250 0.5942 0.00869 0.00302 -0.0229 0.1565 0.9937 3.500 0.6301 0.00884 0.00313 -0.0245 0.1514 0.9957 3.750 0.6653 0.00906 0.00326 -0.0260 0.1445 0.9978 4.000 0.6988 0.00922 0.00339 -0.0272 0.1398 1.0000 4.250 0.7221 0.00937 0.00349 -0.0262 0.1357 1.0000 4.500 0.7469 0.00958 0.00363 -0.0256 0.1303 1.0000 4.750 0.7737 0.00974 0.00377 -0.0254 0.1271 1.0000 5.000 0.8012 0.00991 0.00391 -0.0253 0.1239 1.0000 5.250 0.8288 0.01013 0.00407 -0.0252 0.1202 1.0000 5.500 0.8562 0.01039 0.00429 -0.0251 0.1162 1.0000 5.750 0.8844 0.01055 0.00445 -0.0252 0.1144 1.0000 6.000 0.9124 0.01075 0.00463 -0.0252 0.1121 1.0000 6.250 0.9400 0.01098 0.00482 -0.0252 0.1095 1.0000 6.500 0.9672 0.01128 0.00507 -0.0251 0.1065 1.0000 6.750 0.9945 0.01154 0.00533 -0.0250 0.1045 1.0000 7.000 1.0223 0.01173 0.00553 -0.0250 0.1033 1.0000 7.250 1.0498 0.01195 0.00573 -0.0250 0.1017 1.0000 7.500 1.0770 0.01219 0.00597 -0.0249 0.1000 1.0000 7.750 1.1038 0.01247 0.00622 -0.0248 0.0984 1.0000 8.000 1.1300 0.01281 0.00654 -0.0246 0.0965 1.0000 8.250 1.1554 0.01323 0.00696 -0.0243 0.0946 1.0000 8.500 1.1822 0.01345 0.00721 -0.0242 0.0940 1.0000 8.750 1.2087 0.01370 0.00747 -0.0241 0.0932 1.0000 9.000 1.2349 0.01398 0.00776 -0.0239 0.0923 1.0000 9.250 1.2608 0.01427 0.00806 -0.0237 0.0913 1.0000 9.500 1.2864 0.01457 0.00838 -0.0234 0.0904 1.0000 9.750 1.3116 0.01490 0.00871 -0.0231 0.0894 1.0000 10.000 1.3362 0.01526 0.00908 -0.0228 0.0884 1.0000 10.250 1.3600 0.01569 0.00951 -0.0223 0.0873 1.0000 10.500 1.3821 0.01626 0.01010 -0.0216 0.0860 1.0000 10.750 1.4042 0.01678 0.01065 -0.0210 0.0850 1.0000 11.000 1.4284 0.01709 0.01100 -0.0206 0.0847 1.0000 11.250 1.4520 0.01745 0.01139 -0.0201 0.0842 1.0000 11.500 1.4748 0.01783 0.01181 -0.0195 0.0837 1.0000 11.750 1.4970 0.01825 0.01226 -0.0188 0.0831 1.0000 12.000 1.5186 0.01868 0.01273 -0.0181 0.0825 1.0000 12.250 1.5395 0.01914 0.01323 -0.0173 0.0820 1.0000 12.500 1.5596 0.01962 0.01374 -0.0164 0.0814 1.0000 12.750 1.5785 0.02012 0.01428 -0.0154 0.0808 1.0000 13.000 1.5950 0.02064 0.01484 -0.0139 0.0803 1.0000 13.250 1.6100 0.02123 0.01547 -0.0123 0.0798 1.0000 13.500 1.6242 0.02191 0.01618 -0.0108 0.0793 1.0000 13.750 1.6372 0.02269 0.01701 -0.0092 0.0788 1.0000 14.000 1.6486 0.02361 0.01797 -0.0076 0.0783 1.0000 14.250 1.6578 0.02473 0.01915 -0.0060 0.0776 1.0000 14.500 1.6640 0.02613 0.02062 -0.0042 0.0770 1.0000 14.750 1.6714 0.02752 0.02208 -0.0028 0.0765 1.0000 15.000 1.6839 0.02853 0.02316 -0.0019 0.0764 1.0000 15.250 1.6960 0.02961 0.02431 -0.0011 0.0762 1.0000 15.500 1.7074 0.03078 0.02556 -0.0003 0.0759 1.0000 15.750 1.7178 0.03207 0.02693 0.0003 0.0757 1.0000 16.000 1.7271 0.03351 0.02845 0.0009 0.0754 1.0000 16.250 1.7350 0.03511 0.03012 0.0014 0.0751 1.0000 16.500 1.7420 0.03686 0.03196 0.0018 0.0748 1.0000 16.750 1.7479 0.03876 0.03394 0.0021 0.0745 1.0000 17.000 1.7527 0.04083 0.03609 0.0022 0.0742 1.0000 17.250 1.7564 0.04307 0.03842 0.0022 0.0739 1.0000 17.500 1.7589 0.04551 0.04094 0.0020 0.0736 1.0000 17.750 1.7603 0.04813 0.04366 0.0017 0.0734 1.0000 18.000 1.7605 0.05094 0.04655 0.0012 0.0731 1.0000 18.250 1.7598 0.05395 0.04966 0.0005 0.0728 1.0000 18.500 1.7580 0.05720 0.05299 -0.0003 0.0725 1.0000 18.750 1.7551 0.06065 0.05653 -0.0014 0.0723 1.0000 19.000 1.7510 0.06429 0.06027 -0.0026 0.0720 1.0000 19.250 1.7462 0.06813 0.06419 -0.0039 0.0718 1.0000