XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5635 0.09285 0.08782 -0.0273 1.0000 0.0191 -10.250 -0.5734 0.08549 0.08053 -0.0316 1.0000 0.0185 -10.000 -0.5967 0.07288 0.06793 -0.0407 1.0000 0.0177 -9.750 -0.6374 0.06230 0.05715 -0.0483 1.0000 0.0168 -9.500 -0.6588 0.05797 0.05266 -0.0488 1.0000 0.0167 -9.000 -0.6848 0.05114 0.04534 -0.0455 1.0000 0.0165 -8.750 -0.6916 0.04777 0.04167 -0.0434 1.0000 0.0165 -8.500 -0.6949 0.04461 0.03817 -0.0410 1.0000 0.0165 -8.250 -0.6958 0.04169 0.03496 -0.0383 1.0000 0.0165 -8.000 -0.6943 0.03898 0.03192 -0.0354 1.0000 0.0166 -7.750 -0.6912 0.03638 0.02903 -0.0325 1.0000 0.0168 -7.500 -0.6848 0.03432 0.02674 -0.0299 1.0000 0.0173 -7.250 -0.6758 0.03265 0.02486 -0.0274 1.0000 0.0179 -7.000 -0.6649 0.03115 0.02314 -0.0251 1.0000 0.0189 -6.750 -0.6521 0.02961 0.02134 -0.0229 1.0000 0.0202 -6.500 -0.6376 0.02791 0.01934 -0.0208 1.0000 0.0213 -6.250 -0.6216 0.02624 0.01739 -0.0188 1.0000 0.0221 -6.000 -0.6051 0.02484 0.01574 -0.0168 1.0000 0.0229 -5.750 -0.5903 0.02328 0.01414 -0.0149 1.0000 0.0244 -5.500 -0.5741 0.02222 0.01300 -0.0131 1.0000 0.0262 -5.250 -0.5481 0.02107 0.01167 -0.0131 0.9970 0.0303 -5.000 -0.5190 0.02003 0.01057 -0.0140 0.9930 0.0406 -4.750 -0.4907 0.01902 0.00962 -0.0147 0.9886 0.0619 -4.500 -0.4606 0.01814 0.00890 -0.0159 0.9847 0.0963 -4.250 -0.4328 0.01732 0.00824 -0.0165 0.9801 0.1381 -4.000 -0.4047 0.01648 0.00770 -0.0173 0.9755 0.2071 -3.750 -0.3762 0.01550 0.00727 -0.0183 0.9716 0.3306 -3.500 -0.3529 0.01475 0.00709 -0.0178 0.9662 0.4679 -3.250 -0.3260 0.01436 0.00706 -0.0175 0.9614 0.5731 -3.000 -0.2950 0.01426 0.00716 -0.0177 0.9577 0.6511 -2.750 -0.2697 0.01428 0.00720 -0.0167 0.9518 0.7048 -2.500 -0.2399 0.01435 0.00724 -0.0167 0.9469 0.7466 -2.250 -0.2063 0.01445 0.00727 -0.0174 0.9434 0.7808 -2.000 -0.1818 0.01453 0.00729 -0.0163 0.9367 0.8087 -1.750 -0.1500 0.01463 0.00734 -0.0165 0.9323 0.8344 -1.500 -0.1143 0.01471 0.00735 -0.0177 0.9290 0.8568 -1.250 -0.0868 0.01478 0.00735 -0.0173 0.9222 0.8739 -1.000 -0.0506 0.01482 0.00732 -0.0188 0.9178 0.8880 -0.750 -0.0108 0.01484 0.00728 -0.0211 0.9146 0.9003 -0.500 0.0198 0.01489 0.00729 -0.0216 0.9074 0.9128 -0.250 0.0616 0.01490 0.00726 -0.0244 0.9033 0.9216 0.000 0.1021 0.01490 0.00723 -0.0270 0.8992 0.9306 0.250 0.1376 0.01493 0.00725 -0.0287 0.8921 0.9401 0.500 0.1806 0.01489 0.00721 -0.0317 0.8876 0.9466 0.750 0.2172 0.01489 0.00723 -0.0337 0.8804 0.9552 1.000 0.2596 0.01482 0.00721 -0.0367 0.8744 0.9610 1.250 0.2981 0.01477 0.00720 -0.0389 0.8667 0.9684 1.500 0.3382 0.01464 0.00714 -0.0414 0.8589 0.9746 1.750 0.3744 0.01455 0.00714 -0.0431 0.8482 0.9825 2.000 0.4123 0.01437 0.00704 -0.0451 0.8367 0.9893 2.250 0.4489 0.01416 0.00692 -0.0467 0.8229 0.9968 2.500 0.4743 0.01397 0.00683 -0.0460 0.8055 1.0000 2.750 0.4930 0.01378 0.00669 -0.0439 0.7867 1.0000 3.000 0.5100 0.01364 0.00659 -0.0414 0.7634 1.0000 3.250 0.5292 0.01347 0.00644 -0.0392 0.7369 1.0000 3.500 0.5489 0.01334 0.00630 -0.0371 0.7053 1.0000 3.750 0.5689 0.01330 0.00622 -0.0350 0.6659 1.0000 4.000 0.5885 0.01337 0.00617 -0.0328 0.6163 1.0000 4.250 0.6068 0.01361 0.00621 -0.0306 0.5542 1.0000 4.500 0.6224 0.01410 0.00633 -0.0280 0.4698 1.0000 4.750 0.6350 0.01491 0.00666 -0.0253 0.3693 1.0000 5.000 0.6475 0.01591 0.00715 -0.0228 0.2729 1.0000 5.250 0.6618 0.01693 0.00775 -0.0209 0.1968 1.0000 5.500 0.6782 0.01787 0.00842 -0.0192 0.1469 1.0000 5.750 0.6957 0.01874 0.00914 -0.0177 0.1172 1.0000 6.000 0.7137 0.01961 0.00995 -0.0163 0.0981 1.0000 6.250 0.7317 0.02051 0.01084 -0.0148 0.0858 1.0000 6.500 0.7501 0.02139 0.01175 -0.0134 0.0750 1.0000 6.750 0.7688 0.02233 0.01278 -0.0120 0.0664 1.0000 7.000 0.7866 0.02346 0.01391 -0.0106 0.0592 1.0000 7.250 0.8059 0.02437 0.01492 -0.0095 0.0507 1.0000 7.500 0.8252 0.02539 0.01607 -0.0084 0.0427 1.0000 7.750 0.8427 0.02664 0.01733 -0.0072 0.0370 1.0000 8.000 0.8625 0.02814 0.01904 -0.0059 0.0327 1.0000 8.250 0.8800 0.02945 0.02038 -0.0048 0.0293 1.0000 8.500 0.8989 0.03126 0.02244 -0.0037 0.0262 1.0000 8.750 0.9173 0.03325 0.02471 -0.0025 0.0242 1.0000 9.000 0.9337 0.03530 0.02703 -0.0012 0.0229 1.0000 9.250 0.9479 0.03742 0.02939 0.0002 0.0220 1.0000 9.500 0.9593 0.03984 0.03203 0.0017 0.0212 1.0000 9.750 0.9663 0.04299 0.03543 0.0035 0.0207 1.0000 10.000 0.9680 0.04618 0.03908 0.0059 0.0204 1.0000 10.250 0.9644 0.04944 0.04275 0.0086 0.0203 1.0000 10.500 0.9543 0.05258 0.04623 0.0117 0.0201 1.0000 10.750 0.9392 0.05601 0.04998 0.0144 0.0199 1.0000 11.000 0.9222 0.05978 0.05402 0.0160 0.0198 1.0000 11.250 0.9043 0.06393 0.05840 0.0165 0.0198 1.0000 11.500 0.8859 0.06861 0.06326 0.0157 0.0200 1.0000 11.750 0.8640 0.07435 0.06919 0.0133 0.0200 1.0000 12.000 0.8439 0.08081 0.07578 0.0095 0.0202 1.0000 12.250 0.8219 0.08896 0.08403 0.0039 0.0204 1.0000 12.500 0.8040 0.09763 0.09275 -0.0020 0.0207 1.0000