XFOIL Version 6.96 Calculated polar for: RAF 89 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9225 0.08777 0.08261 -0.0716 1.0000 0.0718 -19.000 -0.9241 0.08474 0.07953 -0.0725 1.0000 0.0726 -18.750 -0.9303 0.08118 0.07595 -0.0736 1.0000 0.0736 -18.500 -0.9352 0.07784 0.07256 -0.0744 1.0000 0.0747 -18.250 -0.9402 0.07451 0.06920 -0.0753 1.0000 0.0758 -18.000 -0.9427 0.07155 0.06619 -0.0759 1.0000 0.0772 -17.750 -0.9451 0.06864 0.06323 -0.0764 1.0000 0.0785 -17.500 -0.9465 0.06589 0.06043 -0.0768 1.0000 0.0796 -17.250 -0.9530 0.06264 0.05715 -0.0773 1.0000 0.0810 -17.000 -0.9579 0.05965 0.05413 -0.0775 1.0000 0.0823 -16.750 -0.9608 0.05695 0.05139 -0.0776 1.0000 0.0838 -16.500 -0.9617 0.05451 0.04889 -0.0776 1.0000 0.0853 -16.250 -0.9458 0.05171 0.04605 -0.0808 0.9984 0.0875 -16.000 -0.9441 0.04867 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0.00392 -0.0429 0.5789 0.3803 -1.250 0.0538 0.01087 0.00386 -0.0412 0.5724 0.3879 -1.000 0.0723 0.01082 0.00381 -0.0393 0.5663 0.3966 -0.500 0.1107 0.01069 0.00373 -0.0358 0.5520 0.4152 0.000 0.1456 0.01056 0.00368 -0.0316 0.5373 0.4417 0.250 0.1600 0.01052 0.00366 -0.0288 0.5288 0.4574 0.500 0.1755 0.01046 0.00367 -0.0263 0.5208 0.4770 0.750 0.1886 0.01045 0.00371 -0.0233 0.5116 0.4970 1.000 0.2006 0.01046 0.00374 -0.0201 0.5036 0.5134 1.250 0.2144 0.01051 0.00378 -0.0172 0.4943 0.5255 1.500 0.2265 0.01059 0.00384 -0.0140 0.4852 0.5358 1.750 0.2423 0.01069 0.00390 -0.0116 0.4763 0.5444 2.000 0.2541 0.01082 0.00402 -0.0085 0.4676 0.5512 2.250 0.2708 0.01094 0.00412 -0.0063 0.4591 0.5578 2.500 0.2848 0.01112 0.00425 -0.0036 0.4511 0.5634 2.750 0.3004 0.01126 0.00438 -0.0013 0.4434 0.5686 3.000 0.3157 0.01141 0.00453 0.0011 0.4360 0.5736 3.250 0.3286 0.01163 0.00471 0.0038 0.4286 0.5783 3.500 0.3466 0.01179 0.00485 0.0056 0.4222 0.5830 3.750 0.3618 0.01199 0.00502 0.0078 0.4156 0.5864 4.000 0.3750 0.01220 0.00522 0.0104 0.4096 0.5904 4.250 0.3927 0.01236 0.00539 0.0121 0.4037 0.5941 4.500 0.4083 0.01256 0.00560 0.0142 0.3978 0.5982 4.750 0.4217 0.01284 0.00584 0.0166 0.3917 0.6021 5.000 0.4387 0.01306 0.00605 0.0183 0.3869 0.6054 5.250 0.4561 0.01329 0.00627 0.0200 0.3816 0.6083 5.500 0.4697 0.01356 0.00655 0.0222 0.3756 0.6123 5.750 0.4830 0.01388 0.00686 0.0244 0.3706 0.6159 6.000 0.5009 0.01410 0.00711 0.0258 0.3659 0.6203 6.250 0.5166 0.01440 0.00742 0.0276 0.3608 0.6247 6.500 0.5308 0.01476 0.00776 0.0295 0.3556 0.6288 6.750 0.5448 0.01514 0.00814 0.0314 0.3508 0.6331 7.000 0.5619 0.01542 0.00847 0.0328 0.3459 0.6377 7.250 0.5775 0.01576 0.00884 0.0344 0.3412 0.6434 7.500 0.5908 0.01621 0.00929 0.0362 0.3363 0.6488 8.000 0.6226 0.01696 0.01012 0.0390 0.3276 0.6631 8.250 0.6373 0.01741 0.01060 0.0405 0.3223 0.6710 8.500 0.6512 0.01790 0.01112 0.0420 0.3178 0.6793 8.750 0.6658 0.01839 0.01165 0.0434 0.3136 0.6885 9.250 0.6982 0.01929 0.01269 0.0456 0.3045 0.7138 9.500 0.7111 0.01992 0.01337 0.0470 0.2997 0.7314 9.750 0.7274 0.02043 0.01397 0.0479 0.2957 0.7537 10.000 0.7466 0.02089 0.01455 0.0484 0.2910 0.7777 10.250 0.7657 0.02152 0.01528 0.0484 0.2860 0.8028 10.500 0.7903 0.02227 0.01613 0.0471 0.2811 0.8320 10.750 0.8452 0.02290 0.01697 0.0402 0.2755 0.8710 11.000 0.9285 0.02400 0.01819 0.0270 0.2676 0.9097 11.250 0.9991 0.02518 0.01942 0.0163 0.2594 0.9501 11.500 1.0277 0.02642 0.02065 0.0137 0.2514 0.9847 11.750 1.0453 0.02790 0.02209 0.0136 0.2448 0.9997 12.000 1.0576 0.02892 0.02310 0.0144 0.2382 1.0000 12.250 1.0636 0.03016 0.02431 0.0159 0.2333 1.0000 12.500 1.0755 0.03107 0.02523 0.0170 0.2295 1.0000 12.750 1.0863 0.03209 0.02625 0.0180 0.2248 1.0000 13.000 1.0937 0.03339 0.02754 0.0192 0.2201 1.0000 13.250 1.1028 0.03458 0.02873 0.0202 0.2165 1.0000 13.500 1.1144 0.03565 0.02982 0.0210 0.2127 1.0000 13.750 1.1237 0.03690 0.03109 0.0218 0.2084 1.0000 14.000 1.1308 0.03835 0.03252 0.0227 0.2042 1.0000 14.250 1.1397 0.03970 0.03389 0.0234 0.2005 1.0000 14.500 1.1493 0.04102 0.03523 0.0241 0.1961 1.0000 14.750 1.1556 0.04263 0.03685 0.0248 0.1915 1.0000 15.000 1.1612 0.04435 0.03856 0.0255 0.1872 1.0000 15.250 1.1705 0.04576 0.04000 0.0260 0.1830 1.0000 15.500 1.1750 0.04764 0.04189 0.0265 0.1784 1.0000 15.750 1.1793 0.04954 0.04380 0.0270 0.1745 1.0000 16.000 1.1866 0.05124 0.04553 0.0274 0.1703 1.0000 16.250 1.1897 0.05332 0.04761 0.0278 0.1653 1.0000 16.500 1.1914 0.05558 0.04989 0.0281 0.1610 1.0000 16.750 1.1962 0.05758 0.05191 0.0284 0.1564 1.0000 17.000 1.1959 0.06012 0.05446 0.0286 0.1515 1.0000 17.250 1.1974 0.06251 0.05688 0.0287 0.1468 1.0000 17.500 1.1976 0.06507 0.05946 0.0287 0.1420 1.0000 17.750 1.1952 0.06793 0.06233 0.0287 0.1377 1.0000 18.000 1.1955 0.07058 0.06501 0.0286 0.1332 1.0000 18.250 1.1929 0.07356 0.06801 0.0285 0.1287 1.0000 18.500 1.1902 0.07658 0.07106 0.0282 0.1248 1.0000 18.750 1.1874 0.07966 0.07417 0.0278 0.1203 1.0000 19.000 1.1809 0.08320 0.07772 0.0274 0.1159 1.0000 19.250 1.1792 0.08624 0.08081 0.0269 0.1125 1.0000