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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9680 0.08738 0.08236 -0.0730 1.0000 0.0812 -19.500 -0.9681 0.08452 0.07945 -0.0739 1.0000 0.0824 -19.250 -0.9664 0.08192 0.07680 -0.0746 1.0000 0.0835 -19.000 -0.9671 0.07898 0.07378 -0.0755 1.0000 0.0846 -18.750 -0.9660 0.07658 0.07141 -0.0759 1.0000 0.0861 -18.500 -0.9676 0.07374 0.06858 -0.0765 1.0000 0.0875 -18.250 -0.9690 0.07091 0.06572 -0.0771 1.0000 0.0890 -18.000 -0.9692 0.06828 0.06303 -0.0776 1.0000 0.0905 -17.750 -0.9684 0.06575 0.06043 -0.0780 1.0000 0.0920 -17.500 -0.9727 0.06283 0.05752 -0.0783 1.0000 0.0937 -17.250 -0.9766 0.05999 0.05468 -0.0785 1.0000 0.0954 -17.000 -0.9790 0.05735 0.05200 -0.0786 1.0000 0.0974 -16.750 -0.9792 0.05497 0.04958 -0.0786 1.0000 0.0996 -16.500 -0.9822 0.05247 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0.5290 0.6124 2.500 0.3345 0.01066 0.00442 -0.0128 0.5205 0.6168 2.750 0.3490 0.01067 0.00446 -0.0101 0.5111 0.6220 3.000 0.3623 0.01078 0.00454 -0.0072 0.5023 0.6269 3.250 0.3768 0.01089 0.00464 -0.0046 0.4932 0.6315 3.500 0.3897 0.01108 0.00475 -0.0017 0.4845 0.6357 3.750 0.4050 0.01122 0.00488 0.0007 0.4761 0.6395 4.000 0.4191 0.01136 0.00500 0.0032 0.4678 0.6444 4.250 0.4344 0.01150 0.00517 0.0056 0.4600 0.6487 4.500 0.4488 0.01169 0.00533 0.0080 0.4524 0.6534 4.750 0.4627 0.01191 0.00551 0.0104 0.4454 0.6577 5.000 0.4787 0.01209 0.00569 0.0125 0.4386 0.6613 5.250 0.4932 0.01229 0.00588 0.0148 0.4315 0.6660 5.500 0.5075 0.01251 0.00611 0.0170 0.4251 0.6709 5.750 0.5235 0.01270 0.00634 0.0190 0.4189 0.6759 6.000 0.5375 0.01297 0.00658 0.0212 0.4127 0.6815 6.250 0.5516 0.01326 0.00684 0.0234 0.4067 0.6870 6.500 0.5676 0.01345 0.00712 0.0252 0.4012 0.6942 6.750 0.5813 0.01373 0.00742 0.0274 0.3953 0.7019 7.000 0.5950 0.01410 0.00773 0.0294 0.3894 0.7092 7.250 0.6110 0.01432 0.00806 0.0311 0.3847 0.7182 7.500 0.6250 0.01462 0.00842 0.0331 0.3791 0.7301 7.750 0.6379 0.01496 0.00880 0.0352 0.3736 0.7443 8.000 0.6521 0.01530 0.00918 0.0371 0.3685 0.7604 8.250 0.6672 0.01560 0.00959 0.0388 0.3637 0.7803 8.500 0.6829 0.01593 0.01002 0.0402 0.3583 0.8037 8.750 0.7033 0.01632 0.01051 0.0406 0.3526 0.8342 9.000 0.7494 0.01669 0.01110 0.0359 0.3470 0.8747 9.250 0.8317 0.01734 0.01188 0.0235 0.3389 0.9084 9.500 0.9061 0.01813 0.01268 0.0128 0.3312 0.9347 9.750 0.9593 0.01883 0.01344 0.0066 0.3247 0.9598 10.000 0.9928 0.01968 0.01425 0.0040 0.3186 0.9819 10.250 1.0255 0.02066 0.01522 0.0016 0.3130 0.9982 10.500 1.0526 0.02139 0.01597 0.0003 0.3072 1.0000 10.750 1.0596 0.02209 0.01663 0.0026 0.3027 1.0000 11.000 1.0653 0.02291 0.01740 0.0050 0.2971 1.0000 11.250 1.0756 0.02361 0.01813 0.0067 0.2919 1.0000 11.500 1.0824 0.02452 0.01901 0.0087 0.2860 1.0000 11.750 1.0894 0.02546 0.01990 0.0106 0.2807 1.0000 12.000 1.1010 0.02625 0.02074 0.0119 0.2761 1.0000 12.250 1.1113 0.02714 0.02162 0.0132 0.2713 1.0000 12.500 1.1189 0.02821 0.02265 0.0148 0.2666 1.0000 12.750 1.1297 0.02914 0.02360 0.0160 0.2625 1.0000 13.000 1.1420 0.03002 0.02452 0.0170 0.2582 1.0000 13.250 1.1510 0.03113 0.02562 0.0181 0.2537 1.0000 13.500 1.1582 0.03237 0.02681 0.0194 0.2492 1.0000 13.750 1.1709 0.03334 0.02783 0.0202 0.2452 1.0000 14.000 1.1803 0.03455 0.02907 0.0211 0.2406 1.0000 14.250 1.1878 0.03588 0.03037 0.0220 0.2360 1.0000 14.500 1.1962 0.03719 0.03168 0.0229 0.2319 1.0000 14.750 1.2066 0.03843 0.03298 0.0236 0.2276 1.0000 15.000 1.2146 0.03984 0.03439 0.0243 0.2231 1.0000 15.250 1.2188 0.04155 0.03606 0.0252 0.2187 1.0000 15.500 1.2289 0.04290 0.03748 0.0257 0.2143 1.0000 15.750 1.2362 0.04446 0.03906 0.0262 0.2099 1.0000 16.000 1.2390 0.04641 0.04098 0.0269 0.2052 1.0000 16.250 1.2472 0.04796 0.04258 0.0273 0.2011 1.0000 16.500 1.2525 0.04982 0.04448 0.0277 0.1965 1.0000 16.750 1.2550 0.05189 0.04653 0.0282 0.1918 1.0000 17.000 1.2592 0.05390 0.04858 0.0285 0.1874 1.0000 17.250 1.2636 0.05591 0.05062 0.0287 0.1826 1.0000 17.500 1.2608 0.05861 0.05331 0.0290 0.1774 1.0000 17.750 1.2664 0.06059 0.05535 0.0291 0.1731 1.0000 18.000 1.2648 0.06329 0.05807 0.0292 0.1679 1.0000 18.250 1.2631 0.06602 0.06079 0.0292 0.1629 1.0000 18.500 1.2628 0.06869 0.06351 0.0291 0.1578 1.0000 18.750 1.2557 0.07208 0.06689 0.0290 0.1526 1.0000 19.000 1.2559 0.07478 0.06965 0.0287 0.1473 1.0000 19.250 1.2472 0.07844 0.07331 0.0284 0.1420 1.0000