XFOIL Version 6.96 Calculated polar for: CLARK YM-18 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.9917 0.08255 0.07909 -0.0770 1.0000 0.0304 -18.750 -1.0037 0.07745 0.07392 -0.0799 1.0000 0.0305 -18.500 -1.0166 0.07231 0.06870 -0.0827 1.0000 0.0306 -18.250 -1.0298 0.06720 0.06350 -0.0855 1.0000 0.0307 -18.000 -1.0422 0.06228 0.05848 -0.0882 1.0000 0.0308 -17.750 -1.0538 0.05747 0.05358 -0.0909 1.0000 0.0310 -17.500 -1.0634 0.05291 0.04893 -0.0934 1.0000 0.0311 -17.250 -1.0713 0.04862 0.04455 -0.0958 1.0000 0.0312 -17.000 -1.0770 0.04469 0.04052 -0.0980 1.0000 0.0314 -16.750 -1.0807 0.04115 0.03688 -0.0998 1.0000 0.0315 -16.500 -1.0826 0.03805 0.03369 -0.1012 1.0000 0.0317 -16.250 -1.0834 0.03536 0.03092 -0.1020 1.0000 0.0319 -16.000 -1.0844 0.03310 0.02857 -0.1020 1.0000 0.0321 -15.750 -1.0873 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0.9186 3.500 0.7236 0.00868 0.00360 -0.0632 0.3497 0.9501 3.750 0.7482 0.00892 0.00379 -0.0625 0.3409 0.9636 4.000 0.7799 0.00911 0.00396 -0.0634 0.3352 0.9712 4.250 0.8096 0.00932 0.00413 -0.0638 0.3301 0.9798 4.500 0.8458 0.00959 0.00435 -0.0657 0.3242 0.9846 4.750 0.8830 0.00983 0.00456 -0.0679 0.3194 0.9889 5.000 0.9205 0.01003 0.00474 -0.0701 0.3148 0.9926 5.250 0.9594 0.01029 0.00495 -0.0727 0.3091 0.9949 5.500 0.9964 0.01060 0.00520 -0.0749 0.3031 0.9977 5.750 1.0357 0.01075 0.00536 -0.0775 0.3003 0.9997 6.000 1.0490 0.01083 0.00545 -0.0747 0.2977 1.0000 6.250 1.0515 0.01090 0.00551 -0.0696 0.2951 1.0000 6.500 1.0594 0.01102 0.00562 -0.0657 0.2921 1.0000 6.750 1.0710 0.01123 0.00580 -0.0626 0.2884 1.0000 7.000 1.0875 0.01145 0.00602 -0.0605 0.2852 1.0000 7.250 1.1093 0.01158 0.00616 -0.0595 0.2831 1.0000 7.500 1.1308 0.01174 0.00634 -0.0585 0.2803 1.0000 7.750 1.1520 0.01196 0.00655 -0.0574 0.2772 1.0000 8.000 1.1724 0.01222 0.00680 -0.0563 0.2740 1.0000 8.250 1.1917 0.01254 0.00711 -0.0550 0.2704 1.0000 8.500 1.2128 0.01281 0.00739 -0.0541 0.2677 1.0000 8.750 1.2359 0.01301 0.00762 -0.0534 0.2656 1.0000 9.000 1.2581 0.01325 0.00788 -0.0527 0.2626 1.0000 9.250 1.2793 0.01355 0.00817 -0.0519 0.2590 1.0000 9.500 1.2988 0.01393 0.00853 -0.0508 0.2548 1.0000 9.750 1.3186 0.01430 0.00891 -0.0499 0.2511 1.0000 10.000 1.3411 0.01456 0.00920 -0.0493 0.2480 1.0000 10.250 1.3619 0.01491 0.00956 -0.0485 0.2438 1.0000 10.500 1.3805 0.01536 0.01000 -0.0475 0.2390 1.0000 10.750 1.3999 0.01580 0.01043 -0.0466 0.2344 1.0000 11.000 1.4200 0.01620 0.01085 -0.0458 0.2291 1.0000 11.250 1.4366 0.01679 0.01141 -0.0446 0.2219 1.0000 11.500 1.4550 0.01730 0.01193 -0.0437 0.2154 1.0000 11.750 1.4697 0.01803 0.01261 -0.0424 0.2064 1.0000 12.000 1.4853 0.01872 0.01328 -0.0412 0.1973 1.0000 12.250 1.4976 0.01962 0.01413 -0.0398 0.1870 1.0000 12.500 1.5076 0.02068 0.01514 -0.0381 0.1760 1.0000 12.750 1.5168 0.02181 0.01623 -0.0365 0.1652 1.0000 13.000 1.5258 0.02299 0.01736 -0.0349 0.1552 1.0000 13.250 1.5331 0.02431 0.01865 -0.0333 0.1451 1.0000 13.500 1.5397 0.02573 0.02003 -0.0317 0.1358 1.0000 13.750 1.5458 0.02721 0.02148 -0.0302 0.1274 1.0000 14.000 1.5538 0.02861 0.02287 -0.0289 0.1207 1.0000 14.250 1.5593 0.03024 0.02449 -0.0276 0.1142 1.0000 14.500 1.5669 0.03176 0.02601 -0.0265 0.1091 1.0000 14.750 1.5711 0.03358 0.02783 -0.0253 0.1041 1.0000 15.000 1.5792 0.03512 0.02940 -0.0245 0.1010 1.0000 15.250 1.5847 0.03694 0.03123 -0.0235 0.0978 1.0000 15.500 1.5873 0.03905 0.03337 -0.0226 0.0946 1.0000 15.750 1.5953 0.04072 0.03509 -0.0220 0.0930 1.0000 16.000 1.6012 0.04261 0.03702 -0.0213 0.0912 1.0000 16.250 1.6045 0.04478 0.03924 -0.0207 0.0893 1.0000 16.500 1.6057 0.04721 0.04170 -0.0201 0.0874 1.0000 16.750 1.6050 0.04989 0.04443 -0.0196 0.0854 1.0000 17.000 1.6108 0.05194 0.04655 -0.0193 0.0844 1.0000 17.250 1.6140 0.05429 0.04896 -0.0190 0.0833 1.0000 17.500 1.6159 0.05680 0.05153 -0.0188 0.0821 1.0000 17.750 1.6156 0.05961 0.05440 -0.0186 0.0810 1.0000 18.000 1.6129 0.06273 0.05758 -0.0186 0.0799 1.0000 18.250 1.6077 0.06615 0.06107 -0.0186 0.0787 1.0000 18.500 1.5993 0.07001 0.06500 -0.0187 0.0774 1.0000 18.750 1.5978 0.07312 0.06818 -0.0189 0.0766 1.0000 19.000 1.5974 0.07613 0.07127 -0.0192 0.0758 1.0000 19.250 1.5948 0.07941 0.07464 -0.0196 0.0749 1.0000