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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.8420 0.04933 0.04724 -0.0494 1.0000 0.0029 -12.000 -0.8608 0.04384 0.04159 -0.0526 1.0000 0.0029 -11.750 -0.8687 0.04064 0.03827 -0.0533 1.0000 0.0030 -11.500 -0.8885 0.03685 0.03428 -0.0525 1.0000 0.0030 -11.250 -0.9027 0.03418 0.03142 -0.0498 1.0000 0.0030 -11.000 -0.9116 0.03195 0.02899 -0.0464 1.0000 0.0030 -10.750 -0.9105 0.02980 0.02663 -0.0442 1.0000 0.0031 -10.500 -0.9074 0.02757 0.02416 -0.0419 1.0000 0.0031 -10.250 -0.8884 0.02569 0.02206 -0.0423 0.9855 0.0032 -10.000 -0.8659 0.02359 0.01969 -0.0433 0.9742 0.0032 -9.750 -0.8425 0.02218 0.01808 -0.0438 0.9644 0.0033 -9.500 -0.8229 0.02072 0.01640 -0.0433 0.9540 0.0033 -9.250 -0.8038 0.01962 0.01510 -0.0424 0.9448 0.0034 -9.000 -0.7840 0.01870 0.01403 -0.0415 0.9373 0.0034 -8.750 -0.7646 0.01769 0.01285 -0.0404 0.9305 0.0034 -8.500 -0.7439 0.01680 0.01181 -0.0395 0.9248 0.0035 -8.250 -0.7221 0.01606 0.01095 -0.0387 0.9194 0.0035 -7.750 -0.6769 0.01472 0.00939 -0.0374 0.9102 0.0037 -7.500 -0.6559 0.01375 0.00827 -0.0365 0.9054 0.0038 -7.250 -0.6335 0.01303 0.00744 -0.0357 0.9013 0.0039 -7.000 -0.6097 0.01244 0.00677 -0.0352 0.8975 0.0039 -6.750 -0.5857 0.01186 0.00611 -0.0346 0.8935 0.0040 -6.500 -0.5611 0.01139 0.00557 -0.0342 0.8896 0.0041 -6.000 -0.5106 0.01059 0.00464 -0.0335 0.8827 0.0045 -5.750 -0.4848 0.01024 0.00425 -0.0332 0.8790 0.0047 -5.500 -0.4588 0.00993 0.00389 -0.0329 0.8754 0.0050 -5.250 -0.4326 0.00967 0.00356 -0.0327 0.8721 0.0053 -5.000 -0.4060 0.00942 0.00328 -0.0325 0.8687 0.0057 -4.750 -0.3793 0.00918 0.00300 -0.0324 0.8649 0.0063 -4.500 -0.3527 0.00895 0.00274 -0.0322 0.8611 0.0076 -4.250 -0.3265 0.00866 0.00248 -0.0320 0.8575 0.0163 -4.000 -0.3002 0.00834 0.00226 -0.0318 0.8538 0.0339 -3.750 -0.2736 0.00809 0.00207 -0.0317 0.8496 0.0519 -3.500 -0.2470 0.00785 0.00191 -0.0316 0.8454 0.0717 -3.250 -0.2202 0.00764 0.00175 -0.0315 0.8415 0.0934 -3.000 -0.1935 0.00737 0.00160 -0.0314 0.8369 0.1260 -2.750 -0.1673 0.00706 0.00145 -0.0313 0.8321 0.1747 -2.500 -0.1425 0.00657 0.00128 -0.0310 0.8276 0.2636 -2.000 -0.0899 0.00597 0.00105 -0.0307 0.8166 0.3817 -1.750 -0.0633 0.00573 0.00097 -0.0306 0.8110 0.4344 -1.500 -0.0365 0.00552 0.00090 -0.0305 0.8041 0.4830 -1.250 -0.0096 0.00536 0.00084 -0.0304 0.7973 0.5243 -1.000 0.0174 0.00520 0.00079 -0.0303 0.7886 0.5636 -0.750 0.0443 0.00507 0.00075 -0.0301 0.7787 0.6005 -0.500 0.0710 0.00496 0.00072 -0.0299 0.7668 0.6378 -0.250 0.0976 0.00487 0.00072 -0.0296 0.7528 0.6767 0.000 0.1244 0.00485 0.00073 -0.0294 0.7368 0.7066 0.250 0.1514 0.00488 0.00074 -0.0292 0.7189 0.7261 0.500 0.1783 0.00493 0.00075 -0.0290 0.6995 0.7409 0.750 0.2054 0.00499 0.00078 -0.0288 0.6777 0.7527 1.000 0.2321 0.00509 0.00081 -0.0286 0.6529 0.7619 1.250 0.2588 0.00521 0.00085 -0.0284 0.6246 0.7701 1.500 0.2852 0.00535 0.00091 -0.0281 0.5919 0.7781 1.750 0.3109 0.00557 0.00098 -0.0278 0.5471 0.7854 2.000 0.3358 0.00586 0.00109 -0.0273 0.4898 0.7930 2.250 0.3609 0.00616 0.00120 -0.0269 0.4353 0.7999 2.500 0.3861 0.00646 0.00133 -0.0265 0.3847 0.8069 2.750 0.4106 0.00684 0.00149 -0.0261 0.3238 0.8136 3.000 0.4357 0.00714 0.00165 -0.0257 0.2768 0.8205 3.500 0.4842 0.00793 0.00204 -0.0248 0.1678 0.8347 3.750 0.5097 0.00820 0.00221 -0.0245 0.1378 0.8422 4.000 0.5347 0.00847 0.00241 -0.0241 0.1101 0.8502 4.250 0.5597 0.00875 0.00261 -0.0237 0.0854 0.8587 4.500 0.5850 0.00898 0.00281 -0.0233 0.0693 0.8683 4.750 0.6098 0.00923 0.00303 -0.0228 0.0541 0.8788 5.000 0.6346 0.00943 0.00324 -0.0223 0.0449 0.8910 5.250 0.6589 0.00963 0.00346 -0.0217 0.0378 0.9067 5.500 0.6831 0.00979 0.00368 -0.0210 0.0336 0.9278 5.750 0.7100 0.01002 0.00394 -0.0209 0.0276 0.9530 6.000 0.7435 0.01032 0.00424 -0.0224 0.0227 0.9728 6.250 0.7765 0.01061 0.00453 -0.0238 0.0186 0.9876 6.500 0.8073 0.01105 0.00490 -0.0249 0.0108 0.9984 6.750 0.8315 0.01143 0.00527 -0.0244 0.0077 1.0000 7.000 0.8547 0.01176 0.00562 -0.0237 0.0070 1.0000 7.250 0.8779 0.01211 0.00600 -0.0229 0.0064 1.0000 7.500 0.9010 0.01248 0.00640 -0.0222 0.0061 1.0000 7.750 0.9237 0.01289 0.00685 -0.0215 0.0057 1.0000 8.000 0.9461 0.01336 0.00736 -0.0207 0.0053 1.0000 8.250 0.9679 0.01389 0.00796 -0.0198 0.0051 1.0000 8.500 0.9901 0.01436 0.00848 -0.0190 0.0050 1.0000 8.750 1.0122 0.01484 0.00902 -0.0182 0.0048 1.0000 9.000 1.0337 0.01537 0.00961 -0.0173 0.0047 1.0000 9.250 1.0548 0.01593 0.01023 -0.0164 0.0046 1.0000 9.500 1.0754 0.01652 0.01090 -0.0154 0.0044 1.0000 9.750 1.0952 0.01717 0.01164 -0.0143 0.0044 1.0000 10.000 1.1144 0.01786 0.01241 -0.0132 0.0042 1.0000 10.250 1.1333 0.01854 0.01316 -0.0120 0.0041 1.0000 10.500 1.1521 0.01919 0.01388 -0.0109 0.0040 1.0000 10.750 1.1695 0.01993 0.01470 -0.0096 0.0038 1.0000 11.000 1.1858 0.02073 0.01559 -0.0081 0.0037 1.0000 11.250 1.2003 0.02157 0.01653 -0.0064 0.0036 1.0000 11.500 1.2116 0.02246 0.01752 -0.0041 0.0036 1.0000 11.750 1.2214 0.02340 0.01856 -0.0018 0.0035 1.0000 12.000 1.2284 0.02453 0.01982 0.0008 0.0035 1.0000 12.250 1.2333 0.02584 0.02125 0.0035 0.0034 1.0000 12.500 1.2374 0.02723 0.02277 0.0059 0.0033 1.0000 12.750 1.2416 0.02865 0.02431 0.0082 0.0033 1.0000 13.000 1.2371 0.03082 0.02667 0.0109 0.0032 1.0000 13.250 1.2343 0.03294 0.02895 0.0130 0.0032 1.0000 13.500 1.2292 0.03538 0.03156 0.0149 0.0032 1.0000 13.750 1.2166 0.03870 0.03508 0.0165 0.0031 1.0000 14.000 1.2182 0.04081 0.03730 0.0171 0.0031 1.0000 14.250 1.2038 0.04482 0.04150 0.0174 0.0031 1.0000 14.500 1.2071 0.04710 0.04388 0.0172 0.0031 1.0000 14.750 1.1842 0.05294 0.04993 0.0157 0.0031 1.0000 15.000 1.1805 0.05672 0.05382 0.0142 0.0031 1.0000 15.250 1.1594 0.06363 0.06091 0.0107 0.0031 1.0000 15.500 1.1433 0.07058 0.06801 0.0065 0.0031 1.0000 15.750 1.1140 0.08112 0.07874 -0.0001 0.0031 1.0000 16.000 0.9405 0.10019 0.09820 -0.0116 0.0033 1.0000 16.250 0.9043 0.11180 0.10995 -0.0180 0.0034 1.0000