XFOIL Version 6.96 Calculated polar for: EPPLER 426 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -0.8607 0.08581 0.08010 -0.0111 1.0000 0.0414 -13.000 -0.8974 0.07469 0.06882 -0.0182 1.0000 0.0412 -12.750 -0.9266 0.06535 0.05933 -0.0247 1.0000 0.0409 -12.500 -0.9515 0.05733 0.05112 -0.0306 1.0000 0.0408 -12.250 -0.9714 0.05093 0.04451 -0.0353 1.0000 0.0411 -12.000 -0.9869 0.04609 0.03947 -0.0380 1.0000 0.0416 -11.750 -0.9964 0.04296 0.03627 -0.0387 1.0000 0.0424 -11.500 -1.0023 0.04061 0.03385 -0.0378 1.0000 0.0436 -11.250 -1.0011 0.03845 0.03156 -0.0370 1.0000 0.0454 -11.000 -0.9965 0.03624 0.02911 -0.0361 1.0000 0.0480 -10.750 -0.9860 0.03482 0.02767 -0.0353 1.0000 0.0509 -10.500 -0.9740 0.03313 0.02575 -0.0345 1.0000 0.0554 -10.250 -0.9585 0.03207 0.02466 -0.0338 1.0000 0.0597 -10.000 -0.9423 0.03081 0.02323 -0.0330 1.0000 0.0658 -9.750 -0.9247 0.02965 0.02182 -0.0323 1.0000 0.0729 -9.500 -0.9055 0.02895 0.02110 -0.0316 1.0000 0.0790 -9.250 -0.8860 0.02801 0.01993 -0.0309 1.0000 0.0861 -9.000 -0.8647 0.02754 0.01942 -0.0302 1.0000 0.0924 -8.750 -0.8434 0.02686 0.01856 -0.0296 1.0000 0.0987 -8.500 -0.8210 0.02647 0.01809 -0.0289 1.0000 0.1045 -8.250 -0.7988 0.02580 0.01720 -0.0283 1.0000 0.1103 -8.000 -0.7756 0.02547 0.01685 -0.0277 1.0000 0.1153 -7.750 -0.7527 0.02479 0.01587 -0.0270 1.0000 0.1213 -7.500 -0.7293 0.02439 0.01551 -0.0264 1.0000 0.1259 -7.250 -0.7057 0.02395 0.01496 -0.0258 1.0000 0.1317 -7.000 -0.6822 0.02328 0.01408 -0.0251 1.0000 0.1369 -6.750 -0.6582 0.02265 0.01346 -0.0245 1.0000 0.1404 -6.500 -0.6341 0.02196 0.01270 -0.0238 1.0000 0.1439 -6.250 -0.6098 0.02128 0.01189 -0.0232 1.0000 0.1480 -6.000 -0.5856 0.02062 0.01111 -0.0225 1.0000 0.1521 -5.750 -0.5617 0.02003 0.01057 -0.0218 1.0000 0.1560 -5.500 -0.5376 0.01947 0.00997 -0.0210 1.0000 0.1605 -5.250 -0.5133 0.01893 0.00932 -0.0203 1.0000 0.1655 -5.000 -0.4897 0.01836 0.00880 -0.0195 1.0000 0.1700 -4.750 -0.4661 0.01789 0.00836 -0.0187 1.0000 0.1755 -4.500 -0.4422 0.01749 0.00788 -0.0178 1.0000 0.1823 -4.250 -0.4192 0.01702 0.00751 -0.0170 1.0000 0.1885 -4.000 -0.3959 0.01665 0.00715 -0.0161 1.0000 0.1958 -3.750 -0.3730 0.01625 0.00680 -0.0152 1.0000 0.2027 -3.500 -0.3505 0.01591 0.00652 -0.0143 1.0000 0.2103 -3.250 -0.3284 0.01560 0.00625 -0.0133 1.0000 0.2182 -3.000 -0.3071 0.01531 0.00604 -0.0123 1.0000 0.2275 -2.750 -0.2683 0.01499 0.00583 -0.0147 0.9873 0.2415 -2.500 -0.2285 0.01465 0.00563 -0.0173 0.9720 0.2606 -2.250 -0.1905 0.01428 0.00543 -0.0194 0.9542 0.2869 -2.000 -0.1531 0.01386 0.00528 -0.0213 0.9349 0.3260 -1.750 -0.1128 0.01343 0.00515 -0.0236 0.9137 0.3868 -1.500 -0.0737 0.01309 0.00504 -0.0253 0.8849 0.4542 -1.250 -0.0393 0.01288 0.00494 -0.0257 0.8482 0.5094 -1.000 -0.0109 0.01276 0.00488 -0.0249 0.8107 0.5561 -0.500 0.0414 0.01265 0.00482 -0.0227 0.7505 0.6350 -0.250 0.0672 0.01264 0.00480 -0.0215 0.7239 0.6688 0.000 0.0927 0.01263 0.00480 -0.0203 0.6971 0.7023 0.250 0.1179 0.01263 0.00481 -0.0191 0.6707 0.7352 0.500 0.1429 0.01264 0.00481 -0.0177 0.6437 0.7680 0.750 0.1679 0.01264 0.00482 -0.0163 0.6158 0.8031 1.000 0.1941 0.01265 0.00484 -0.0151 0.5877 0.8457 1.250 0.2276 0.01269 0.00486 -0.0152 0.5558 0.9001 1.500 0.2718 0.01280 0.00486 -0.0178 0.5154 0.9540 1.750 0.3167 0.01298 0.00482 -0.0211 0.4703 0.9929 2.000 0.3428 0.01322 0.00484 -0.0209 0.4320 1.0000 2.250 0.3648 0.01351 0.00491 -0.0198 0.3969 1.0000 2.500 0.3876 0.01383 0.00502 -0.0189 0.3641 1.0000 2.750 0.4109 0.01419 0.00517 -0.0180 0.3365 1.0000 3.000 0.4347 0.01456 0.00537 -0.0173 0.3148 1.0000 3.250 0.4589 0.01494 0.00560 -0.0166 0.2978 1.0000 3.500 0.4834 0.01532 0.00586 -0.0159 0.2833 1.0000 3.750 0.5081 0.01572 0.00615 -0.0153 0.2711 1.0000 4.000 0.5328 0.01614 0.00646 -0.0147 0.2606 1.0000 4.250 0.5581 0.01651 0.00681 -0.0142 0.2507 1.0000 4.500 0.5828 0.01698 0.00717 -0.0136 0.2426 1.0000 4.750 0.6085 0.01736 0.00758 -0.0131 0.2342 1.0000 5.000 0.6333 0.01785 0.00798 -0.0126 0.2273 1.0000 5.250 0.6590 0.01826 0.00845 -0.0121 0.2196 1.0000 5.500 0.6841 0.01873 0.00889 -0.0116 0.2126 1.0000 5.750 0.7094 0.01922 0.00940 -0.0111 0.2060 1.0000 6.000 0.7346 0.01969 0.00992 -0.0106 0.1991 1.0000 6.250 0.7593 0.02025 0.01041 -0.0101 0.1931 1.0000 6.500 0.7845 0.02073 0.01104 -0.0096 0.1859 1.0000 6.750 0.8091 0.02126 0.01157 -0.0090 0.1799 1.0000 7.000 0.8337 0.02185 0.01223 -0.0085 0.1737 1.0000 7.250 0.8581 0.02239 0.01286 -0.0079 0.1670 1.0000 7.500 0.8820 0.02300 0.01341 -0.0074 0.1618 1.0000 7.750 0.9060 0.02361 0.01424 -0.0068 0.1550 1.0000 8.000 0.9295 0.02415 0.01482 -0.0062 0.1492 1.0000 8.250 0.9527 0.02483 0.01561 -0.0056 0.1436 1.0000 8.500 0.9756 0.02544 0.01635 -0.0049 0.1373 1.0000 8.750 0.9979 0.02604 0.01692 -0.0042 0.1326 1.0000 9.000 1.0199 0.02681 0.01794 -0.0035 0.1263 1.0000 9.250 1.0414 0.02743 0.01862 -0.0028 0.1215 1.0000 9.500 1.0622 0.02828 0.01960 -0.0020 0.1167 1.0000 9.750 1.0825 0.02913 0.02060 -0.0012 0.1117 1.0000 10.000 1.1022 0.02988 0.02136 -0.0003 0.1078 1.0000 10.250 1.1205 0.03102 0.02272 0.0006 0.1034 1.0000 10.500 1.1382 0.03207 0.02392 0.0016 0.0993 1.0000 10.750 1.1553 0.03304 0.02492 0.0026 0.0961 1.0000 11.000 1.1703 0.03444 0.02650 0.0036 0.0928 1.0000 11.250 1.1833 0.03587 0.02818 0.0048 0.0891 1.0000 11.500 1.1961 0.03699 0.02939 0.0060 0.0858 1.0000 11.750 1.2074 0.03820 0.03060 0.0073 0.0829 1.0000 12.000 1.2113 0.04002 0.03276 0.0089 0.0794 1.0000 12.250 1.2133 0.04151 0.03441 0.0107 0.0765 1.0000 12.500 1.2157 0.04283 0.03576 0.0122 0.0739 1.0000 12.750 1.2123 0.04497 0.03805 0.0132 0.0715 1.0000 13.000 1.2038 0.04799 0.04134 0.0133 0.0692 1.0000 13.250 1.1955 0.05124 0.04477 0.0126 0.0670 1.0000 13.500 1.1878 0.05481 0.04847 0.0112 0.0654 1.0000 13.750 1.1817 0.05835 0.05203 0.0093 0.0635 1.0000 14.000 1.1635 0.06427 0.05816 0.0059 0.0626 1.0000 14.250 1.1374 0.07205 0.06618 0.0010 0.0620 1.0000 14.500 1.1053 0.08150 0.07585 -0.0050 0.0621 1.0000 14.750 1.0619 0.09388 0.08840 -0.0128 0.0627 1.0000