XFOIL Version 6.96 Calculated polar for: EPPLER 682 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -0.5305 0.05328 0.05024 -0.1091 0.7667 0.0059 -13.000 -0.5560 0.04708 0.04388 -0.1124 0.7649 0.0059 -12.750 -0.5918 0.04131 0.03784 -0.1126 0.7630 0.0061 -12.500 -0.6203 0.03713 0.03341 -0.1105 0.7612 0.0061 -12.250 -0.6329 0.03453 0.03063 -0.1081 0.7597 0.0061 -12.000 -0.6437 0.03214 0.02804 -0.1053 0.7583 0.0060 -11.750 -0.6492 0.03011 0.02583 -0.1024 0.7572 0.0062 -11.500 -0.6493 0.02850 0.02405 -0.0997 0.7561 0.0063 -11.250 -0.6514 0.02669 0.02205 -0.0966 0.7549 0.0062 -11.000 -0.6444 0.02560 0.02081 -0.0942 0.7537 0.0064 -10.750 -0.6354 0.02471 0.01980 -0.0919 0.7526 0.0065 -10.500 -0.6311 0.02326 0.01817 -0.0889 0.7514 0.0065 -10.250 -0.6188 0.02274 0.01754 -0.0868 0.7503 0.0066 -10.000 -0.6051 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-0.1894 0.01129 0.00474 -0.0721 0.7322 0.0093 -5.000 -0.1650 0.01096 0.00438 -0.0717 0.7311 0.0095 -4.750 -0.1405 0.01064 0.00403 -0.0713 0.7300 0.0099 -4.500 -0.1152 0.01041 0.00377 -0.0711 0.7288 0.0103 -4.250 -0.0893 0.01022 0.00357 -0.0710 0.7276 0.0107 -4.000 -0.0632 0.01002 0.00337 -0.0708 0.7266 0.0111 -3.750 -0.0370 0.00984 0.00319 -0.0707 0.7253 0.0116 -3.500 -0.0105 0.00968 0.00302 -0.0707 0.7239 0.0122 -3.250 0.0160 0.00952 0.00286 -0.0707 0.7224 0.0131 -3.000 0.0426 0.00936 0.00270 -0.0706 0.7209 0.0145 -2.750 0.0694 0.00922 0.00256 -0.0706 0.7195 0.0165 -2.500 0.0949 0.00896 0.00241 -0.0704 0.7179 0.0423 -2.250 0.1201 0.00870 0.00229 -0.0703 0.7163 0.0798 -2.000 0.1449 0.00840 0.00217 -0.0700 0.7147 0.1358 -1.750 0.1689 0.00805 0.00206 -0.0697 0.7129 0.2138 -1.500 0.1920 0.00759 0.00195 -0.0692 0.7114 0.3140 -1.250 0.2133 0.00696 0.00182 -0.0686 0.7096 0.4571 -1.000 0.2324 0.00600 0.00160 -0.0676 0.7075 0.6653 -0.750 0.2569 0.00582 0.00182 -0.0670 0.7055 0.7842 -0.500 0.2858 0.00593 0.00193 -0.0672 0.7034 0.8045 -0.250 0.3147 0.00605 0.00201 -0.0675 0.7013 0.8148 0.000 0.3433 0.00614 0.00210 -0.0677 0.6992 0.8202 0.250 0.3717 0.00627 0.00222 -0.0679 0.6969 0.8257 0.500 0.4007 0.00636 0.00231 -0.0682 0.6941 0.8313 0.750 0.4286 0.00641 0.00239 -0.0683 0.6906 0.8346 1.000 0.4570 0.00645 0.00241 -0.0686 0.6869 0.8364 1.250 0.4855 0.00646 0.00239 -0.0689 0.6833 0.8373 1.500 0.5145 0.00645 0.00240 -0.0694 0.6791 0.8379 1.750 0.5432 0.00644 0.00239 -0.0698 0.6737 0.8384 2.000 0.5715 0.00645 0.00236 -0.0701 0.6679 0.8389 2.250 0.5999 0.00645 0.00237 -0.0705 0.6600 0.8396 2.500 0.6277 0.00647 0.00237 -0.0707 0.6508 0.8403 2.750 0.6549 0.00651 0.00237 -0.0708 0.6385 0.8408 3.000 0.6811 0.00659 0.00238 -0.0708 0.6218 0.8413 3.250 0.7057 0.00672 0.00244 -0.0704 0.6018 0.8419 3.500 0.7294 0.00691 0.00253 -0.0699 0.5817 0.8424 3.750 0.7525 0.00712 0.00265 -0.0692 0.5589 0.8430 4.000 0.7745 0.00737 0.00280 -0.0684 0.5367 0.8436 4.250 0.7960 0.00763 0.00297 -0.0675 0.5124 0.8443 4.500 0.8172 0.00789 0.00314 -0.0665 0.4914 0.8450 4.750 0.8387 0.00812 0.00331 -0.0656 0.4718 0.8455 5.000 0.8590 0.00838 0.00350 -0.0645 0.4515 0.8460 5.250 0.8778 0.00867 0.00370 -0.0631 0.4313 0.8465 5.500 0.8959 0.00896 0.00391 -0.0616 0.4101 0.8469 5.750 0.9092 0.00928 0.00414 -0.0591 0.3871 0.8476 6.000 0.9178 0.00967 0.00442 -0.0557 0.3599 0.8484 6.500 0.9338 0.01075 0.00525 -0.0491 0.3016 0.8500 6.750 0.9387 0.01147 0.00580 -0.0456 0.2667 0.8509 7.000 0.9435 0.01226 0.00642 -0.0422 0.2309 0.8517 7.250 0.9544 0.01289 0.00696 -0.0399 0.2089 0.8526 7.500 0.9646 0.01359 0.00755 -0.0376 0.1850 0.8535 7.750 0.9743 0.01435 0.00820 -0.0353 0.1613 0.8543 8.000 0.9870 0.01502 0.00880 -0.0336 0.1435 0.8550 8.250 0.9967 0.01586 0.00951 -0.0315 0.1209 0.8557 8.500 1.0083 0.01664 0.01021 -0.0297 0.1017 0.8564 8.750 1.0185 0.01751 0.01098 -0.0278 0.0822 0.8571 9.000 1.0290 0.01840 0.01177 -0.0260 0.0636 0.8578 9.250 1.0391 0.01933 0.01261 -0.0243 0.0465 0.8585 9.500 1.0513 0.02016 0.01339 -0.0228 0.0359 0.8591 9.750 1.0622 0.02110 0.01427 -0.0212 0.0244 0.8597 10.000 1.0703 0.02223 0.01532 -0.0194 0.0112 0.8603 10.250 1.0840 0.02304 0.01613 -0.0183 0.0086 0.8608 10.500 1.0980 0.02384 0.01695 -0.0172 0.0077 0.8613 10.750 1.1124 0.02464 0.01778 -0.0162 0.0069 0.8618 11.000 1.1272 0.02543 0.01861 -0.0153 0.0066 0.8622 11.250 1.1414 0.02623 0.01945 -0.0144 0.0063 0.8628 11.500 1.1551 0.02709 0.02036 -0.0134 0.0061 0.8635 11.750 1.1671 0.02809 0.02140 -0.0123 0.0056 0.8642 12.000 1.1802 0.02903 0.02239 -0.0114 0.0055 0.8648 12.250 1.1914 0.03012 0.02353 -0.0103 0.0052 0.8655 12.500 1.2023 0.03126 0.02473 -0.0093 0.0052 0.8663 12.750 1.2123 0.03250 0.02604 -0.0083 0.0050 0.8671 13.000 1.2241 0.03363 0.02722 -0.0074 0.0048 0.8679 13.250 1.2344 0.03490 0.02855 -0.0066 0.0048 0.8686 13.500 1.2451 0.03617 0.02988 -0.0058 0.0047 0.8693 13.750 1.2556 0.03748 0.03125 -0.0051 0.0046 0.8700 14.000 1.2640 0.03901 0.03285 -0.0043 0.0046 0.8707 14.250 1.2722 0.04058 0.03449 -0.0035 0.0044 0.8714 14.500 1.2803 0.04222 0.03620 -0.0029 0.0044 0.8721 14.750 1.2873 0.04399 0.03804 -0.0023 0.0043 0.8728 15.000 1.2941 0.04583 0.03995 -0.0018 0.0041 0.8735 15.250 1.3013 0.04768 0.04187 -0.0014 0.0041 0.8742 15.500 1.3054 0.04992 0.04419 -0.0009 0.0040 0.8749 15.750 1.3114 0.05199 0.04633 -0.0007 0.0039 0.8755 16.000 1.3153 0.05434 0.04876 -0.0005 0.0039 0.8761 16.250 1.3180 0.05691 0.05142 -0.0004 0.0039 0.8767 16.750 1.3221 0.06240 0.05708 -0.0007 0.0038 0.8782 17.000 1.3235 0.06533 0.06010 -0.0010 0.0037 0.8790 17.250 1.3230 0.06856 0.06343 -0.0014 0.0037 0.8797 17.500 1.3213 0.07207 0.06705 -0.0021 0.0037 0.8805 17.750 1.3178 0.07590 0.07097 -0.0029 0.0035 0.8813 18.000 1.3134 0.08000 0.07519 -0.0040 0.0035 0.8820 18.250 1.3087 0.08421 0.07950 -0.0052 0.0034 0.8827 18.500 1.2993 0.08925 0.08466 -0.0069 0.0034 0.8833 18.750 1.2912 0.09424 0.08977 -0.0087 0.0033 0.8840