XFOIL Version 6.94 Calculated polar for: EPPLER 654 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6316 0.01160 0.00619 -0.1363 0.6666 0.7462 0.500 0.6858 0.01195 0.00657 -0.1361 0.6623 0.7580 1.000 0.7399 0.01202 0.00668 -0.1360 0.6575 0.7678 1.500 0.7953 0.01211 0.00677 -0.1360 0.6523 0.7773 2.000 0.8541 0.01210 0.00672 -0.1369 0.6473 0.7855 2.500 0.9117 0.01236 0.00694 -0.1375 0.6415 0.7923 3.000 0.9644 0.01233 0.00701 -0.1373 0.6361 0.7998 3.500 1.0193 0.01226 0.00698 -0.1374 0.6294 0.8061 4.000 1.0764 0.01216 0.00688 -0.1379 0.6232 0.8121 4.500 1.1311 0.01227 0.00702 -0.1381 0.6161 0.8192 5.000 1.1824 0.01220 0.00705 -0.1376 0.6077 0.8253 5.500 1.2365 0.01207 0.00694 -0.1375 0.5991 0.8320 6.000 1.2839 0.01211 0.00710 -0.1363 0.5884 0.8393 6.500 1.3328 0.01203 0.00705 -0.1353 0.5768 0.8462 7.000 1.3723 0.01213 0.00731 -0.1325 0.5625 0.8552 7.500 1.4101 0.01226 0.00750 -0.1295 0.5456 0.8640 8.000 1.4316 0.01252 0.00782 -0.1233 0.5247 0.8755 8.500 1.4454 0.01309 0.00843 -0.1160 0.4991 0.8906 9.000 1.4469 0.01410 0.00943 -0.1072 0.4684 0.9126 9.500 1.4429 0.01560 0.01094 -0.0986 0.4359 1.0000 10.000 1.4441 0.01821 0.01341 -0.0928 0.4007 1.0000 10.500 1.4446 0.02117 0.01628 -0.0874 0.3682 1.0000 11.000 1.4433 0.02452 0.01953 -0.0824 0.3366 1.0000 11.500 1.4422 0.02814 0.02305 -0.0780 0.3073 1.0000 12.000 1.4471 0.03165 0.02651 -0.0746 0.2794 1.0000 12.500 1.4511 0.03546 0.03026 -0.0715 0.2520 1.0000 13.000 1.4556 0.03948 0.03420 -0.0688 0.2266 1.0000 13.500 1.4610 0.04367 0.03834 -0.0667 0.2030 1.0000 14.000 1.4694 0.04784 0.04249 -0.0650 0.1807 1.0000 14.500 1.4777 0.05217 0.04679 -0.0636 0.1596 1.0000 15.000 1.4845 0.05689 0.05151 -0.0626 0.1408 1.0000 15.500 1.4901 0.06196 0.05658 -0.0619 0.1239 1.0000 16.000 1.4950 0.06731 0.06195 -0.0615 0.1085 1.0000 16.500 1.4985 0.07306 0.06772 -0.0614 0.0948 1.0000 17.500 1.5006 0.08591 0.08069 -0.0626 0.0723 1.0000 18.000 1.5004 0.09283 0.08770 -0.0639 0.0632 1.0000 19.000 1.4939 0.10811 0.10319 -0.0678 0.0491 1.0000 20.000 1.4838 0.12441 0.11975 -0.0735 0.0387 1.0000 20.500 1.4792 0.13255 0.12806 -0.0770 0.0346 1.0000 21.000 1.4724 0.14105 0.13670 -0.0809 0.0312 1.0000 21.500 1.4631 0.14996 0.14572 -0.0855 0.0282 1.0000 22.000 1.4593 0.15796 0.15390 -0.0899 0.0254 1.0000 22.500 1.4523 0.16643 0.16251 -0.0949 0.0230 1.0000 23.000 1.4440 0.17511 0.17129 -0.1003 0.0209 1.0000 23.500 1.4397 0.18309 0.17945 -0.1055 0.0188 1.0000 24.000 1.4313 0.19174 0.18819 -0.1114 0.0172 1.0000 24.500 1.4269 0.19972 0.19635 -0.1170 0.0155 1.0000 25.000 1.4189 0.20823 0.20493 -0.1232 0.0142 1.0000 25.500 1.4135 0.21638 0.21328 -0.1293 0.0129 1.0000 26.000 1.4071 0.22452 0.22148 -0.1356 0.0119 1.0000 26.500 1.4016 0.23257 0.22970 -0.1419 0.0108 1.0000 27.000 1.3964 0.24052 0.23776 -0.1482 0.0098 1.0000 27.500 1.3912 0.24838 0.24572 -0.1546 0.0089 1.0000 28.000 1.3845 0.25676 0.25425 -0.1613 0.0081 1.0000 28.500 1.3814 0.26409 0.26161 -0.1675 0.0073 1.0000 29.000 1.3730 0.27297 0.27067 -0.1745 0.0066 1.0000 29.500 1.3652 0.28181 0.27964 -0.1815 0.0060 1.0000 30.000 1.3661 0.28791 0.28573 -0.1871 0.0054 1.0000 30.500 1.3397 0.30300 0.30111 -0.1972 0.0049 1.0000 32.000 0.9745 0.48575 0.48468 -0.2139 0.0051 1.0000 32.500 0.9764 0.49777 0.49671 -0.2168 0.0045 1.0000 33.000 0.9784 0.50784 0.50680 -0.2197 0.0040 1.0000 33.500 0.9798 0.51674 0.51573 -0.2225 0.0038 1.0000 34.000 0.9812 0.52646 0.52546 -0.2250 0.0037 1.0000 34.500 0.9813 0.54264 0.54164 -0.2282 0.0034 1.0000 35.000 0.9818 0.55351 0.55254 -0.2309 0.0032 1.0000 35.500 0.9820 0.56440 0.56344 -0.2336 0.0029 1.0000 36.000 0.9818 0.57428 0.57335 -0.2363 0.0027 1.0000 36.500 0.9811 0.58353 0.58262 -0.2389 0.0025 1.0000 37.000 0.9801 0.59211 0.59123 -0.2414 0.0024 1.0000 38.000 0.9772 0.61216 0.61131 -0.2463 0.0024 1.0000 38.500 0.9753 0.62318 0.62234 -0.2488 0.0024 1.0000 39.000 0.9734 0.63391 0.63309 -0.2513 0.0023 1.0000 39.500 0.9714 0.64447 0.64367 -0.2535 0.0022 1.0000 40.000 0.9687 0.65342 0.65264 -0.2558 0.0021 1.0000 40.500 0.9656 0.66228 0.66153 -0.2581 0.0020 1.0000 41.000 0.9623 0.67079 0.67005 -0.2603 0.0019 1.0000 41.500 0.9586 0.67903 0.67832 -0.2624 0.0018 1.0000 42.000 0.9545 0.68672 0.68603 -0.2645 0.0017 1.0000 42.500 0.9501 0.69381 0.69314 -0.2666 0.0016 1.0000 43.000 0.9454 0.70066 0.70001 -0.2686 0.0015 1.0000 43.500 0.9403 0.70701 0.70638 -0.2706 0.0014 1.0000 44.000 0.9347 0.71270 0.71209 -0.2726 0.0014 1.0000 45.500 0.9173 0.73220 0.73165 -0.2780 0.0013 1.0000 46.000 0.9114 0.73885 0.73831 -0.2797 0.0013 1.0000 46.500 0.9054 0.74516 0.74464 -0.2813 0.0013 1.0000 47.000 0.8987 0.74995 0.74945 -0.2829 0.0013 1.0000 47.500 0.8920 0.75494 0.75445 -0.2844 0.0012 1.0000 48.000 0.8849 0.75909 0.75863 -0.2859 0.0011 1.0000 48.500 0.8774 0.76276 0.76231 -0.2874 0.0010 1.0000 49.000 0.8697 0.76583 0.76540 -0.2888 0.0009 1.0000 49.500 0.8617 0.76832 0.76791 -0.2902 0.0009 1.0000 50.000 0.8535 0.77049 0.77009 -0.2915 0.0008 1.0000 50.500 0.8451 0.77218 0.77180 -0.2928 0.0007 1.0000 51.000 0.8364 0.77319 0.77283 -0.2941 0.0007 1.0000 51.500 0.8274 0.77353 0.77319 -0.2953 0.0006 1.0000 52.000 0.8180 0.77332 0.77299 -0.2965 0.0006 1.0000 52.500 0.8082 0.77230 0.77198 -0.2976 0.0006 1.0000 54.500 0.7709 0.77276 0.77249 -0.3012 0.0006 1.0000 55.000 0.7611 0.77116 0.77091 -0.3020 0.0005 1.0000 55.500 0.7512 0.76950 0.76927 -0.3027 0.0005 1.0000 56.000 0.7412 0.76723 0.76701 -0.3034 0.0005 1.0000 56.500 0.7310 0.76447 0.76426 -0.3040 0.0005 1.0000 57.000 0.7206 0.76125 0.76105 -0.3046 0.0005 1.0000 57.500 0.7100 0.75732 0.75713 -0.3051 0.0004 1.0000 58.000 0.6994 0.75326 0.75309 -0.3056 0.0003 1.0000 58.500 0.6885 0.74844 0.74828 -0.3060 0.0003 1.0000 59.000 0.6775 0.74308 0.74293 -0.3064 0.0002 1.0000 59.500 0.6664 0.73740 0.73726 -0.3068 0.0002 1.0000 60.000 0.6552 0.73120 0.73107 -0.3071 0.0002 1.0000