XFOIL Version 6.96 Calculated polar for: EPPLER 485 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.5948 0.09404 0.08893 -0.0280 1.0000 0.0218 -11.750 -0.6166 0.08353 0.07842 -0.0347 1.0000 0.0212 -11.500 -0.6489 0.07279 0.06757 -0.0425 1.0000 0.0201 -11.250 -0.6769 0.06558 0.06019 -0.0471 1.0000 0.0200 -11.000 -0.7041 0.05990 0.05432 -0.0489 1.0000 0.0198 -10.750 -0.7251 0.05578 0.04998 -0.0486 1.0000 0.0198 -10.500 -0.7441 0.05222 0.04622 -0.0469 1.0000 0.0198 -10.250 -0.7589 0.04942 0.04317 -0.0440 1.0000 0.0200 -10.000 -0.7709 0.04677 0.04027 -0.0405 1.0000 0.0203 -9.750 -0.7773 0.04395 0.03713 -0.0374 1.0000 0.0207 -9.500 -0.7799 0.04109 0.03390 -0.0342 1.0000 0.0213 -9.250 -0.7773 0.03841 0.03084 -0.0314 1.0000 0.0218 -9.000 -0.7711 0.03583 0.02781 -0.0286 1.0000 0.0226 -8.750 -0.7609 0.03373 0.02556 -0.0264 1.0000 0.0233 -8.500 -0.7495 0.03228 0.02404 -0.0243 1.0000 0.0245 -8.250 -0.7372 0.03114 0.02277 -0.0222 1.0000 0.0263 -8.000 -0.7234 0.02973 0.02110 -0.0200 1.0000 0.0288 -7.750 -0.7102 0.02822 0.01950 -0.0178 1.0000 0.0307 -7.500 -0.6977 0.02717 0.01841 -0.0156 1.0000 0.0329 -7.250 -0.6846 0.02624 0.01736 -0.0133 1.0000 0.0364 -7.000 -0.6732 0.02513 0.01618 -0.0106 1.0000 0.0395 -6.750 -0.6632 0.02426 0.01531 -0.0079 1.0000 0.0426 -6.500 -0.6523 0.02355 0.01449 -0.0051 1.0000 0.0473 -6.250 -0.6360 0.02265 0.01362 -0.0037 0.9978 0.0530 -6.000 -0.6040 0.02166 0.01255 -0.0052 0.9905 0.0633 -5.750 -0.5714 0.02074 0.01164 -0.0068 0.9834 0.0769 -5.500 -0.5412 0.01991 0.01083 -0.0079 0.9750 0.0950 -5.250 -0.5093 0.01909 0.01012 -0.0094 0.9678 0.1207 -5.000 -0.4793 0.01832 0.00949 -0.0104 0.9595 0.1574 -4.750 -0.4491 0.01750 0.00892 -0.0115 0.9519 0.2123 -4.500 -0.4193 0.01667 0.00843 -0.0125 0.9442 0.2863 -4.250 -0.3926 0.01585 0.00803 -0.0128 0.9360 0.3788 -4.000 -0.3651 0.01512 0.00776 -0.0129 0.9284 0.4842 -3.750 -0.3390 0.01471 0.00775 -0.0121 0.9198 0.5794 -3.500 -0.3061 0.01463 0.00787 -0.0122 0.9133 0.6557 -3.250 -0.2766 0.01471 0.00797 -0.0118 0.9045 0.7047 -3.000 -0.2423 0.01486 0.00805 -0.0121 0.8977 0.7399 -2.750 -0.2141 0.01501 0.00813 -0.0115 0.8880 0.7668 -2.500 -0.1804 0.01518 0.00819 -0.0118 0.8808 0.7885 -2.250 -0.1534 0.01533 0.00823 -0.0110 0.8706 0.8074 -2.000 -0.1246 0.01547 0.00827 -0.0105 0.8611 0.8236 -1.750 -0.0911 0.01563 0.00832 -0.0108 0.8528 0.8367 -1.500 -0.0600 0.01579 0.00839 -0.0108 0.8424 0.8480 -1.250 -0.0286 0.01587 0.00837 -0.0109 0.8328 0.8586 -1.000 -0.0002 0.01589 0.00830 -0.0106 0.8227 0.8695 -0.750 0.0338 0.01596 0.00829 -0.0113 0.8114 0.8768 -0.500 0.0622 0.01596 0.00822 -0.0111 0.8001 0.8858 -0.250 0.0966 0.01597 0.00814 -0.0120 0.7894 0.8923 0.000 0.1250 0.01594 0.00804 -0.0119 0.7778 0.9002 0.250 0.1591 0.01593 0.00798 -0.0129 0.7650 0.9057 0.500 0.1848 0.01589 0.00789 -0.0124 0.7520 0.9138 0.750 0.2208 0.01586 0.00780 -0.0138 0.7385 0.9181 1.000 0.2502 0.01582 0.00772 -0.0140 0.7246 0.9246 1.250 0.2814 0.01577 0.00763 -0.0146 0.7101 0.9299 1.500 0.3162 0.01572 0.00754 -0.0160 0.6945 0.9342 1.750 0.3433 0.01569 0.00747 -0.0158 0.6789 0.9407 2.000 0.3769 0.01564 0.00741 -0.0169 0.6621 0.9449 2.250 0.4102 0.01561 0.00732 -0.0180 0.6445 0.9492 2.500 0.4375 0.01561 0.00729 -0.0180 0.6266 0.9552 2.750 0.4703 0.01560 0.00728 -0.0191 0.6063 0.9592 3.000 0.5024 0.01561 0.00724 -0.0200 0.5858 0.9636 3.250 0.5300 0.01567 0.00727 -0.0201 0.5650 0.9692 3.500 0.5623 0.01572 0.00729 -0.0212 0.5421 0.9732 3.750 0.5932 0.01581 0.00734 -0.0220 0.5186 0.9777 4.000 0.6212 0.01596 0.00742 -0.0223 0.4953 0.9829 4.250 0.6533 0.01609 0.00754 -0.0234 0.4697 0.9868 4.500 0.6830 0.01629 0.00768 -0.0242 0.4448 0.9915 4.750 0.7128 0.01652 0.00785 -0.0250 0.4202 0.9960 5.000 0.7414 0.01678 0.00808 -0.0256 0.3953 1.0000 5.250 0.7573 0.01708 0.00835 -0.0237 0.3757 1.0000 5.500 0.7730 0.01739 0.00864 -0.0217 0.3559 1.0000 5.750 0.7879 0.01773 0.00896 -0.0196 0.3373 1.0000 6.000 0.8022 0.01810 0.00929 -0.0174 0.3199 1.0000 6.250 0.8157 0.01849 0.00967 -0.0151 0.3030 1.0000 6.500 0.8290 0.01888 0.01006 -0.0128 0.2870 1.0000 6.750 0.8417 0.01929 0.01047 -0.0103 0.2714 1.0000 7.000 0.8539 0.01973 0.01090 -0.0078 0.2565 1.0000 7.250 0.8659 0.02018 0.01136 -0.0052 0.2425 1.0000 7.500 0.8777 0.02067 0.01183 -0.0027 0.2289 1.0000 7.750 0.8897 0.02118 0.01237 -0.0002 0.2158 1.0000 8.000 0.9025 0.02170 0.01292 0.0021 0.2029 1.0000 8.250 0.9157 0.02227 0.01352 0.0043 0.1900 1.0000 8.500 0.9294 0.02288 0.01416 0.0063 0.1780 1.0000 8.750 0.9430 0.02354 0.01485 0.0083 0.1664 1.0000 9.000 0.9560 0.02424 0.01559 0.0102 0.1554 1.0000 9.250 0.9680 0.02501 0.01636 0.0122 0.1451 1.0000 9.500 0.9812 0.02577 0.01721 0.0140 0.1345 1.0000 9.750 0.9927 0.02660 0.01810 0.0160 0.1251 1.0000 10.000 1.0002 0.02752 0.01898 0.0185 0.1174 1.0000 10.250 1.0104 0.02841 0.02001 0.0205 0.1086 1.0000 10.500 1.0177 0.02947 0.02110 0.0226 0.1015 1.0000 10.750 1.0258 0.03057 0.02230 0.0245 0.0945 1.0000 11.000 1.0321 0.03185 0.02366 0.0263 0.0883 1.0000 11.250 1.0388 0.03316 0.02508 0.0279 0.0822 1.0000 11.500 1.0427 0.03471 0.02665 0.0295 0.0777 1.0000 11.750 1.0488 0.03625 0.02836 0.0307 0.0721 1.0000 12.000 1.0510 0.03803 0.03019 0.0319 0.0680 1.0000 12.250 1.0543 0.03995 0.03224 0.0329 0.0640 1.0000 12.500 1.0569 0.04198 0.03443 0.0336 0.0600 1.0000 12.750 1.0565 0.04427 0.03678 0.0341 0.0568 1.0000 13.000 1.0560 0.04677 0.03936 0.0344 0.0540 1.0000 13.250 1.0558 0.04941 0.04222 0.0346 0.0508 1.0000 13.500 1.0538 0.05225 0.04522 0.0343 0.0483 1.0000 13.750 1.0490 0.05547 0.04851 0.0337 0.0460 1.0000 14.000 1.0447 0.05885 0.05196 0.0330 0.0441 1.0000 14.250 1.0394 0.06263 0.05600 0.0320 0.0423 1.0000 14.500 1.0326 0.06672 0.06028 0.0306 0.0405 1.0000 14.750 1.0246 0.07111 0.06481 0.0288 0.0390 1.0000 15.000 1.0161 0.07576 0.06958 0.0267 0.0377 1.0000 15.250 1.0075 0.08057 0.07448 0.0244 0.0365 1.0000 15.500 0.9991 0.08546 0.07940 0.0221 0.0353 1.0000 15.750 0.9852 0.09183 0.08601 0.0188 0.0346 1.0000 16.000 0.9688 0.09895 0.09334 0.0148 0.0341 1.0000 16.250 0.9493 0.10700 0.10160 0.0103 0.0336 1.0000 16.500 0.9267 0.11614 0.11091 0.0051 0.0335 1.0000 16.750 0.8998 0.12673 0.12166 -0.0009 0.0338 1.0000 17.000 0.8605 0.14128 0.13630 -0.0090 0.0344 1.0000