XFOIL Version 6.96 Calculated polar for: EPPLER 857 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.5383 0.11204 0.10755 -0.0611 1.0000 0.0159 -16.000 -0.5645 0.10336 0.09870 -0.0653 1.0000 0.0158 -15.750 -0.5832 0.09655 0.09174 -0.0684 1.0000 0.0158 -15.500 -0.5983 0.09063 0.08569 -0.0711 1.0000 0.0160 -15.250 -0.6104 0.08554 0.08048 -0.0731 1.0000 0.0161 -15.000 -0.6208 0.08089 0.07572 -0.0749 1.0000 0.0162 -14.750 -0.6306 0.07660 0.07133 -0.0763 1.0000 0.0164 -14.500 -0.6389 0.07273 0.06734 -0.0774 1.0000 0.0166 -14.250 -0.6461 0.06922 0.06374 -0.0782 1.0000 0.0168 -14.000 -0.6530 0.06597 0.06041 -0.0787 1.0000 0.0169 -13.750 -0.6607 0.06286 0.05721 -0.0789 1.0000 0.0172 -13.500 -0.6678 0.06014 0.05447 -0.0788 1.0000 0.0174 -13.250 -0.6711 0.05747 0.05176 -0.0792 0.9995 0.0174 -13.000 -0.6577 0.05422 0.04844 -0.0835 0.9962 0.0178 -12.750 -0.6441 0.05111 0.04526 -0.0876 0.9926 0.0183 -12.500 -0.6311 0.04813 0.04219 -0.0912 0.9878 0.0189 -12.250 -0.6147 0.04539 0.03933 -0.0950 0.9836 0.0195 -12.000 -0.6030 0.04280 0.03664 -0.0974 0.9765 0.0200 -11.750 -0.5930 0.04019 0.03398 -0.0997 0.9677 0.0206 -11.500 -0.5875 0.03778 0.03153 -0.1008 0.9550 0.0212 -11.250 -0.5813 0.03559 0.02928 -0.1016 0.9400 0.0218 -11.000 -0.5723 0.03346 0.02706 -0.1027 0.9256 0.0228 -10.750 -0.5604 0.03134 0.02484 -0.1043 0.9118 0.0237 -10.500 -0.5449 0.02929 0.02271 -0.1065 0.8980 0.0252 -10.250 -0.5259 0.02733 0.02061 -0.1091 0.8842 0.0269 -10.000 -0.4969 0.02552 0.01870 -0.1127 0.8712 0.0290 -9.750 -0.4612 0.02399 0.01704 -0.1166 0.8564 0.0321 -9.500 -0.4197 0.02267 0.01558 -0.1213 0.8409 0.0360 -9.250 -0.3745 0.02150 0.01430 -0.1267 0.8239 0.0416 -9.000 -0.3377 0.02056 0.01323 -0.1300 0.8049 0.0472 -8.750 -0.3088 0.01983 0.01238 -0.1315 0.7861 0.0534 -8.500 -0.2848 0.01922 0.01167 -0.1318 0.7682 0.0601 -8.250 -0.2630 0.01870 0.01105 -0.1315 0.7516 0.0676 -8.000 -0.2420 0.01824 0.01050 -0.1309 0.7362 0.0762 -7.750 -0.2211 0.01781 0.00998 -0.1302 0.7219 0.0856 -7.500 -0.2015 0.01740 0.00950 -0.1291 0.7077 0.0956 -7.250 -0.1814 0.01699 0.00903 -0.1282 0.6948 0.1070 -7.000 -0.1611 0.01658 0.00856 -0.1272 0.6827 0.1201 -6.750 -0.1412 0.01613 0.00811 -0.1262 0.6709 0.1365 -6.500 -0.1204 0.01571 0.00769 -0.1254 0.6605 0.1586 -6.250 -0.0998 0.01526 0.00728 -0.1245 0.6498 0.1867 -6.000 -0.0792 0.01480 0.00691 -0.1236 0.6399 0.2241 -5.750 -0.0578 0.01445 0.00666 -0.1227 0.6298 0.2681 -5.500 -0.0345 0.01427 0.00653 -0.1220 0.6203 0.3041 -5.250 -0.0101 0.01422 0.00643 -0.1214 0.6109 0.3303 -5.000 0.0150 0.01421 0.00635 -0.1208 0.6025 0.3503 -4.750 0.0402 0.01424 0.00630 -0.1203 0.5941 0.3665 -4.500 0.0656 0.01429 0.00627 -0.1197 0.5866 0.3795 -4.250 0.0912 0.01432 0.00620 -0.1192 0.5784 0.3898 -4.000 0.1167 0.01439 0.00615 -0.1187 0.5710 0.3993 -3.750 0.1424 0.01440 0.00608 -0.1182 0.5634 0.4070 -3.500 0.1677 0.01447 0.00607 -0.1176 0.5559 0.4153 -3.250 0.1936 0.01455 0.00602 -0.1172 0.5497 0.4248 -3.000 0.2192 0.01461 0.00607 -0.1167 0.5431 0.4329 -2.750 0.2451 0.01471 0.00602 -0.1163 0.5370 0.4421 -2.500 0.2707 0.01477 0.00605 -0.1158 0.5315 0.4483 -2.250 0.2965 0.01480 0.00605 -0.1153 0.5254 0.4540 -2.000 0.3223 0.01485 0.00598 -0.1149 0.5196 0.4592 -1.750 0.3480 0.01491 0.00592 -0.1145 0.5144 0.4635 -1.500 0.3737 0.01492 0.00594 -0.1141 0.5088 0.4672 -1.250 0.3994 0.01496 0.00594 -0.1137 0.5037 0.4712 -1.000 0.4251 0.01504 0.00592 -0.1133 0.4992 0.4759 -0.750 0.4514 0.01513 0.00590 -0.1130 0.4950 0.4806 -0.500 0.4771 0.01515 0.00593 -0.1126 0.4904 0.4841 -0.250 0.5024 0.01520 0.00598 -0.1122 0.4858 0.4879 0.000 0.5276 0.01529 0.00601 -0.1117 0.4814 0.4924 0.250 0.5535 0.01541 0.00603 -0.1114 0.4776 0.4973 0.500 0.5790 0.01548 0.00608 -0.1110 0.4734 0.5017 0.750 0.6042 0.01554 0.00617 -0.1105 0.4695 0.5054 1.000 0.6293 0.01563 0.00626 -0.1101 0.4659 0.5098 1.250 0.6547 0.01576 0.00633 -0.1097 0.4625 0.5150 1.500 0.6807 0.01591 0.00640 -0.1094 0.4594 0.5202 1.750 0.7051 0.01598 0.00653 -0.1088 0.4557 0.5245 2.000 0.7293 0.01608 0.00666 -0.1082 0.4520 0.5291 2.250 0.7536 0.01620 0.00678 -0.1076 0.4485 0.5344 2.500 0.7784 0.01635 0.00688 -0.1072 0.4455 0.5404 2.750 0.8037 0.01650 0.00702 -0.1068 0.4428 0.5457 3.000 0.8282 0.01664 0.00720 -0.1063 0.4402 0.5515 3.250 0.8514 0.01677 0.00737 -0.1055 0.4371 0.5576 3.500 0.8742 0.01690 0.00755 -0.1047 0.4339 0.5636 3.750 0.8968 0.01703 0.00772 -0.1038 0.4308 0.5702 4.000 0.9203 0.01720 0.00789 -0.1032 0.4280 0.5780 4.250 0.9450 0.01739 0.00807 -0.1027 0.4256 0.5853 4.500 0.9693 0.01758 0.00830 -0.1023 0.4232 0.5934 4.750 0.9909 0.01776 0.00855 -0.1013 0.4206 0.6018 5.000 1.0123 0.01794 0.00883 -0.1003 0.4178 0.6110 5.250 1.0340 0.01813 0.00909 -0.0993 0.4150 0.6218 5.500 1.0558 0.01832 0.00934 -0.0984 0.4123 0.6334 5.750 1.0784 0.01853 0.00959 -0.0976 0.4099 0.6458 6.000 1.1026 0.01876 0.00984 -0.0972 0.4077 0.6600 6.250 1.1250 0.01899 0.01015 -0.0964 0.4056 0.6758 6.500 1.1436 0.01922 0.01053 -0.0949 0.4032 0.6945 7.000 1.1813 0.01964 0.01124 -0.0921 0.3980 0.7460 7.250 1.2000 0.01981 0.01157 -0.0906 0.3954 0.7870 7.500 1.2230 0.01987 0.01187 -0.0899 0.3931 0.8888 7.750 1.2510 0.02012 0.01212 -0.0904 0.3910 1.0000 8.000 1.2758 0.02048 0.01245 -0.0903 0.3890 1.0000 8.250 1.2918 0.02087 0.01293 -0.0886 0.3867 1.0000 8.500 1.3080 0.02128 0.01341 -0.0871 0.3841 1.0000 8.750 1.3250 0.02168 0.01387 -0.0857 0.3814 1.0000 9.000 1.3425 0.02208 0.01431 -0.0844 0.3789 1.0000 9.250 1.3614 0.02249 0.01474 -0.0833 0.3768 1.0000 9.500 1.3821 0.02288 0.01514 -0.0826 0.3747 1.0000 9.750 1.4058 0.02325 0.01549 -0.0823 0.3727 1.0000 10.000 1.4179 0.02381 0.01615 -0.0803 0.3702 1.0000 10.250 1.4287 0.02442 0.01688 -0.0782 0.3675 1.0000 10.500 1.4411 0.02502 0.01756 -0.0764 0.3649 1.0000 10.750 1.4545 0.02560 0.01821 -0.0748 0.3623 1.0000 11.000 1.4688 0.02614 0.01881 -0.0733 0.3598 1.0000 11.250 1.4870 0.02662 0.01930 -0.0725 0.3574 1.0000 11.500 1.5056 0.02712 0.01980 -0.0717 0.3549 1.0000 11.750 1.5054 0.02818 0.02104 -0.0686 0.3516 1.0000 12.000 1.5089 0.02919 0.02217 -0.0662 0.3480 1.0000 12.250 1.5157 0.03009 0.02315 -0.0643 0.3445 1.0000 12.500 1.5284 0.03077 0.02383 -0.0630 0.3412 1.0000 12.750 1.5404 0.03156 0.02465 -0.0617 0.3380 1.0000 13.000 1.5338 0.03333 0.02660 -0.0590 0.3339 1.0000 13.250 1.5331 0.03489 0.02828 -0.0570 0.3298 1.0000 13.500 1.5394 0.03609 0.02953 -0.0556 0.3260 1.0000 13.750 1.5534 0.03684 0.03027 -0.0548 0.3226 1.0000 14.000 1.5394 0.03965 0.03328 -0.0526 0.3180 1.0000 14.250 1.5339 0.04200 0.03576 -0.0511 0.3135 1.0000 14.500 1.5394 0.04352 0.03732 -0.0502 0.3094 1.0000 14.750 1.5402 0.04555 0.03942 -0.0493 0.3053 1.0000 15.000 1.5207 0.04958 0.04363 -0.0481 0.2995 1.0000 15.250 1.5197 0.05197 0.04608 -0.0474 0.2947 1.0000 15.500 1.5195 0.05436 0.04852 -0.0469 0.2899 1.0000 15.750 1.4920 0.05986 0.05421 -0.0465 0.2833 1.0000 16.000 1.4955 0.06201 0.05637 -0.0463 0.2781 1.0000 16.250 1.4708 0.06761 0.06211 -0.0464 0.2712 1.0000 16.500 1.4599 0.07169 0.06626 -0.0466 0.2644 1.0000 16.750 1.4488 0.07589 0.07053 -0.0470 0.2578 1.0000 17.000 1.4307 0.08113 0.07585 -0.0476 0.2498 1.0000 17.250 1.4206 0.08542 0.08021 -0.0483 0.2426 1.0000 17.500 1.4098 0.08986 0.08470 -0.0490 0.2343 1.0000 17.750 1.3962 0.09479 0.08969 -0.0500 0.2264 1.0000 18.000 1.3990 0.09739 0.09228 -0.0505 0.2185 1.0000