XFOIL Version 6.96 Calculated polar for: EPPLER 334 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3091 0.09067 0.08740 -0.0338 1.0000 0.0196 -8.250 -0.3112 0.08729 0.08409 -0.0354 1.0000 0.0196 -8.000 -0.3182 0.08384 0.08072 -0.0375 1.0000 0.0196 -7.750 -0.2995 0.08001 0.07691 -0.0389 0.9741 0.0200 -7.250 -0.2415 0.06903 0.06558 -0.0570 0.8509 0.0208 -7.000 -0.2320 0.06526 0.06160 -0.0599 0.8130 0.0216 -6.750 -0.2263 0.06195 0.05810 -0.0610 0.7837 0.0219 -6.500 -0.2204 0.05871 0.05468 -0.0615 0.7610 0.0223 -6.250 -0.2127 0.05459 0.05020 -0.0621 0.7430 0.0237 -6.000 -0.2026 0.05135 0.04667 -0.0614 0.7261 0.0239 -5.750 -0.1915 0.04817 0.04316 -0.0603 0.7110 0.0239 -5.500 -0.1808 0.04503 0.03992 -0.0594 0.6961 0.0242 -5.250 -0.1676 0.04255 0.03729 -0.0585 0.6820 0.0246 -5.000 -0.1528 0.03926 0.03376 -0.0570 0.6696 0.0186 -4.750 -0.1356 0.03598 0.03006 -0.0552 0.6584 0.0193 -4.250 -0.1000 0.02948 0.02276 -0.0513 0.6369 0.0157 -4.000 -0.0801 0.02760 0.02062 -0.0501 0.6257 0.0154 -3.750 -0.0586 0.02557 0.01826 -0.0487 0.6149 0.0149 -3.500 -0.0359 0.02350 0.01581 -0.0473 0.6051 0.0144 -3.250 -0.0117 0.02150 0.01337 -0.0460 0.5955 0.0139 -3.000 0.0138 0.01980 0.01129 -0.0449 0.5861 0.0136 -2.750 0.0396 0.01853 0.00971 -0.0440 0.5767 0.0136 -2.500 0.0658 0.01751 0.00847 -0.0433 0.5670 0.0137 -2.250 0.0914 0.01667 0.00746 -0.0425 0.5584 0.0140 -2.000 0.1168 0.01596 0.00664 -0.0418 0.5497 0.0144 -1.750 0.1414 0.01536 0.00592 -0.0409 0.5419 0.0152 -1.500 0.1659 0.01490 0.00535 -0.0401 0.5333 0.0159 -1.250 0.1902 0.01451 0.00492 -0.0393 0.5257 0.0177 -1.000 0.2151 0.01424 0.00460 -0.0386 0.5178 0.0215 -0.750 0.2397 0.01397 0.00425 -0.0379 0.5113 0.0275 -0.500 0.2644 0.01364 0.00396 -0.0372 0.5039 0.0463 -0.250 0.2856 0.01300 0.00376 -0.0361 0.4975 0.1848 0.000 0.2990 0.01157 0.00466 -0.0310 0.4916 0.9291 0.250 0.4221 0.01222 0.00486 -0.0493 0.4804 0.9775 0.500 0.4654 0.01224 0.00474 -0.0525 0.4728 0.9845 0.750 0.4947 0.01228 0.00464 -0.0530 0.4666 0.9866 1.000 0.5253 0.01230 0.00455 -0.0537 0.4609 0.9883 1.250 0.5552 0.01233 0.00450 -0.0543 0.4550 0.9902 1.500 0.5840 0.01240 0.00445 -0.0547 0.4498 0.9921 1.750 0.6127 0.01246 0.00445 -0.0551 0.4440 0.9940 2.000 0.6417 0.01252 0.00445 -0.0555 0.4386 0.9955 2.250 0.6706 0.01261 0.00444 -0.0559 0.4338 0.9971 2.500 0.6996 0.01268 0.00449 -0.0564 0.4285 0.9987 2.750 0.7276 0.01277 0.00456 -0.0566 0.4233 1.0000 3.000 0.7502 0.01290 0.00462 -0.0558 0.4190 1.0000 3.250 0.7730 0.01303 0.00473 -0.0549 0.4145 1.0000 3.500 0.7957 0.01315 0.00486 -0.0540 0.4097 1.0000 3.750 0.8180 0.01329 0.00499 -0.0531 0.4052 1.0000 4.000 0.8401 0.01346 0.00511 -0.0521 0.4014 1.0000 4.250 0.8623 0.01359 0.00529 -0.0512 0.3964 1.0000 4.500 0.8842 0.01375 0.00546 -0.0502 0.3920 1.0000 4.750 0.9058 0.01393 0.00563 -0.0491 0.3879 1.0000 5.000 0.9273 0.01411 0.00583 -0.0481 0.3837 1.0000 5.250 0.9486 0.01428 0.00605 -0.0470 0.3789 1.0000 5.500 0.9695 0.01446 0.00624 -0.0458 0.3745 1.0000 5.750 0.9900 0.01468 0.00646 -0.0446 0.3705 1.0000 6.000 1.0105 0.01486 0.00673 -0.0433 0.3656 1.0000 6.250 1.0304 0.01505 0.00696 -0.0420 0.3606 1.0000 6.500 1.0499 0.01528 0.00717 -0.0406 0.3563 1.0000 6.750 1.0693 0.01548 0.00748 -0.0392 0.3513 1.0000 7.000 1.0882 0.01568 0.00775 -0.0377 0.3461 1.0000 7.250 1.1065 0.01592 0.00798 -0.0360 0.3414 1.0000 7.500 1.1248 0.01614 0.00831 -0.0345 0.3360 1.0000 7.750 1.1426 0.01636 0.00860 -0.0328 0.3304 1.0000 8.000 1.1601 0.01661 0.00886 -0.0310 0.3254 1.0000 8.250 1.1780 0.01684 0.00923 -0.0294 0.3191 1.0000 8.500 1.1953 0.01710 0.00953 -0.0277 0.3131 1.0000 8.750 1.2132 0.01737 0.00988 -0.0262 0.3064 1.0000 9.000 1.2309 0.01764 0.01022 -0.0246 0.2991 1.0000 9.250 1.2489 0.01795 0.01061 -0.0232 0.2916 1.0000 9.500 1.2664 0.01828 0.01100 -0.0217 0.2837 1.0000 9.750 1.2842 0.01863 0.01145 -0.0204 0.2753 1.0000 10.000 1.3002 0.01904 0.01190 -0.0187 0.2669 1.0000 10.250 1.3165 0.01946 0.01241 -0.0172 0.2573 1.0000 10.500 1.3312 0.01993 0.01295 -0.0155 0.2476 1.0000 10.750 1.3431 0.02048 0.01354 -0.0134 0.2377 1.0000 11.000 1.3521 0.02108 0.01419 -0.0109 0.2270 1.0000 11.250 1.3607 0.02176 0.01492 -0.0084 0.2161 1.0000 11.500 1.3672 0.02258 0.01579 -0.0059 0.2050 1.0000 11.750 1.3720 0.02356 0.01680 -0.0035 0.1941 1.0000 12.000 1.3743 0.02477 0.01803 -0.0012 0.1831 1.0000 12.250 1.3752 0.02620 0.01949 0.0008 0.1722 1.0000 12.500 1.3757 0.02784 0.02119 0.0025 0.1613 1.0000 12.750 1.3743 0.02979 0.02318 0.0038 0.1513 1.0000 13.000 1.3711 0.03207 0.02551 0.0048 0.1427 1.0000 13.250 1.3677 0.03457 0.02806 0.0054 0.1341 1.0000 13.500 1.3640 0.03725 0.03081 0.0058 0.1262 1.0000 13.750 1.3567 0.04044 0.03404 0.0059 0.1194 1.0000 14.000 1.3521 0.04348 0.03716 0.0058 0.1122 1.0000 14.250 1.3434 0.04705 0.04078 0.0055 0.1061 1.0000 14.500 1.3368 0.05050 0.04432 0.0051 0.1000 1.0000 14.750 1.3269 0.05442 0.04830 0.0044 0.0948 1.0000 15.000 1.3203 0.05806 0.05203 0.0038 0.0894 1.0000 15.250 1.3103 0.06227 0.05630 0.0028 0.0851 1.0000 15.500 1.3036 0.06617 0.06029 0.0018 0.0800 1.0000 15.750 1.2946 0.07050 0.06467 0.0005 0.0757 1.0000 16.000 1.2868 0.07477 0.06902 -0.0008 0.0716 1.0000 16.250 1.2801 0.07899 0.07333 -0.0021 0.0675 1.0000 16.500 1.2704 0.08373 0.07812 -0.0038 0.0641 1.0000 16.750 1.2652 0.08790 0.08239 -0.0052 0.0602 1.0000