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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0190 0.08236 0.07789 -0.0718 1.0000 0.0598 -19.500 -1.0300 0.07826 0.07375 -0.0730 1.0000 0.0607 -19.250 -1.0356 0.07489 0.07032 -0.0739 1.0000 0.0613 -19.000 -1.0425 0.07143 0.06681 -0.0747 1.0000 0.0619 -18.750 -1.0490 0.06804 0.06337 -0.0754 1.0000 0.0626 -18.500 -1.0534 0.06496 0.06023 -0.0759 1.0000 0.0633 -18.250 -1.0564 0.06208 0.05730 -0.0763 1.0000 0.0639 -18.000 -1.0592 0.05927 0.05443 -0.0767 1.0000 0.0646 -17.750 -1.0496 0.05635 0.05146 -0.0792 0.9994 0.0654 -17.500 -1.0377 0.05352 0.04858 -0.0819 0.9984 0.0663 -17.250 -1.0414 0.05066 0.04569 -0.0813 0.9884 0.0673 -17.000 -1.0366 0.04801 0.04300 -0.0826 0.9806 0.0683 -16.750 -1.0214 0.04560 0.04054 -0.0852 0.9628 0.0695 -16.500 -0.9882 0.04304 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0.4051 0.5225 2.750 0.3059 0.00947 0.00340 -0.0019 0.3994 0.5321 3.000 0.3221 0.00963 0.00353 0.0003 0.3929 0.5403 3.250 0.3403 0.00976 0.00366 0.0021 0.3881 0.5452 3.500 0.3585 0.00987 0.00378 0.0039 0.3826 0.5509 3.750 0.3754 0.01003 0.00393 0.0059 0.3768 0.5568 4.000 0.3908 0.01024 0.00411 0.0082 0.3710 0.5610 4.250 0.4109 0.01037 0.00424 0.0095 0.3670 0.5641 4.500 0.4283 0.01053 0.00440 0.0114 0.3615 0.5680 4.750 0.4434 0.01074 0.00461 0.0136 0.3560 0.5720 5.000 0.4597 0.01096 0.00481 0.0155 0.3513 0.5755 5.250 0.4783 0.01113 0.00500 0.0171 0.3473 0.5785 5.500 0.4957 0.01135 0.00521 0.0187 0.3425 0.5814 5.750 0.5110 0.01165 0.00547 0.0207 0.3367 0.5841 6.000 0.5270 0.01194 0.00574 0.0225 0.3324 0.5859 6.250 0.5451 0.01214 0.00597 0.0240 0.3285 0.5900 6.500 0.5617 0.01240 0.00625 0.0257 0.3241 0.5938 6.750 0.5761 0.01275 0.00659 0.0276 0.3189 0.5973 7.000 0.5918 0.01309 0.00693 0.0293 0.3143 0.6006 7.250 0.6094 0.01340 0.00724 0.0307 0.3103 0.6037 7.500 0.6266 0.01374 0.00758 0.0320 0.3061 0.6062 7.750 0.6423 0.01414 0.00797 0.0336 0.3017 0.6088 8.000 0.6562 0.01459 0.00843 0.0353 0.2970 0.6131 8.250 0.6747 0.01491 0.00878 0.0363 0.2934 0.6170 8.500 0.6911 0.01534 0.00922 0.0376 0.2886 0.6213 8.750 0.7060 0.01585 0.00973 0.0390 0.2838 0.6259 9.000 0.7222 0.01634 0.01022 0.0402 0.2796 0.6297 9.250 0.7398 0.01678 0.01070 0.0411 0.2755 0.6354 9.500 0.7566 0.01729 0.01122 0.0420 0.2707 0.6401 9.750 0.7716 0.01791 0.01184 0.0431 0.2653 0.6448 10.000 0.7893 0.01846 0.01241 0.0438 0.2620 0.6497 10.500 0.8249 0.01964 0.01365 0.0448 0.2516 0.6657 11.000 0.8629 0.02100 0.01511 0.0449 0.2401 0.6963 11.250 0.8818 0.02190 0.01606 0.0444 0.2319 0.7214 11.500 0.9067 0.02267 0.01693 0.0430 0.2250 0.7502 11.750 0.9316 0.02362 0.01794 0.0413 0.2184 0.7758 12.000 0.9683 0.02434 0.01876 0.0378 0.2142 0.7996 12.250 1.0006 0.02519 0.01971 0.0348 0.2086 0.8272 12.500 1.0345 0.02623 0.02093 0.0311 0.2033 0.8772 12.750 1.1240 0.02739 0.02229 0.0168 0.1959 0.9600 13.000 1.1485 0.02870 0.02358 0.0148 0.1904 0.9902 13.250 1.1537 0.02995 0.02483 0.0173 0.1865 0.9990 13.500 1.1774 0.03121 0.02609 0.0156 0.1818 1.0000 13.750 1.1852 0.03249 0.02736 0.0167 0.1770 1.0000 14.000 1.1950 0.03367 0.02854 0.0176 0.1734 1.0000 14.250 1.2036 0.03498 0.02986 0.0185 0.1688 1.0000 14.500 1.2101 0.03644 0.03130 0.0195 0.1636 1.0000 14.750 1.2179 0.03788 0.03274 0.0203 0.1596 1.0000 15.000 1.2262 0.03929 0.03416 0.0210 0.1553 1.0000 15.250 1.2299 0.04109 0.03594 0.0219 0.1497 1.0000 15.500 1.2369 0.04268 0.03755 0.0226 0.1454 1.0000 15.750 1.2426 0.04437 0.03923 0.0232 0.1407 1.0000 16.000 1.2454 0.04636 0.04123 0.0239 0.1364 1.0000 16.250 1.2506 0.04818 0.04305 0.0244 0.1314 1.0000 16.500 1.2501 0.05054 0.04541 0.0250 0.1267 1.0000 16.750 1.2559 0.05237 0.04726 0.0253 0.1227 1.0000 17.000 1.2543 0.05492 0.04981 0.0258 0.1178 1.0000 17.250 1.2576 0.05703 0.05194 0.0260 0.1141 1.0000 17.500 1.2554 0.05974 0.05465 0.0263 0.1092 1.0000 17.750 1.2549 0.06231 0.05724 0.0264 0.1054 1.0000 18.000 1.2539 0.06499 0.05994 0.0265 0.1014 1.0000 18.250 1.2500 0.06799 0.06296 0.0265 0.0979 1.0000 18.500 1.2504 0.07059 0.06559 0.0264 0.0947 1.0000 18.750 1.2471 0.07364 0.06868 0.0262 0.0916 1.0000 19.000 1.2443 0.07667 0.07172 0.0260 0.0886 1.0000 19.250 1.2422 0.07967 0.07477 0.0256 0.0864 1.0000