XFOIL Version 6.96 Calculated polar for: EPPLER 549 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.5749 0.11793 0.11602 -0.0451 1.0000 0.0061 -16.000 -0.5870 0.11035 0.10841 -0.0489 1.0000 0.0062 -15.750 -0.6141 0.09913 0.09706 -0.0552 1.0000 0.0062 -15.500 -0.6196 0.09372 0.09163 -0.0582 1.0000 0.0064 -15.250 -0.6727 0.07918 0.07673 -0.0659 1.0000 0.0056 -15.000 -0.6889 0.07297 0.07040 -0.0690 1.0000 0.0055 -14.750 -0.7117 0.06637 0.06364 -0.0718 1.0000 0.0055 -14.500 -0.7321 0.06068 0.05779 -0.0737 1.0000 0.0054 -14.250 -0.7511 0.05563 0.05256 -0.0749 1.0000 0.0053 -14.000 -0.7643 0.05164 0.04842 -0.0753 1.0000 0.0053 -13.750 -0.7772 0.04793 0.04455 -0.0753 1.0000 0.0052 -13.500 -0.7927 0.04405 0.04046 -0.0747 1.0000 0.0051 -13.250 -0.8002 0.04115 0.03740 -0.0738 1.0000 0.0051 -13.000 -0.8015 0.03902 0.03517 -0.0729 1.0000 0.0050 -12.750 -0.8071 0.03644 0.03241 -0.0714 1.0000 0.0050 -12.500 -0.8089 0.03435 0.03018 -0.0697 1.0000 0.0049 -12.250 -0.8097 0.03247 0.02817 -0.0678 1.0000 0.0049 -12.000 -0.8024 0.03093 0.02654 -0.0670 0.9997 0.0049 -11.750 -0.7785 0.02892 0.02439 -0.0695 0.9974 0.0048 -11.500 -0.7559 0.02716 0.02252 -0.0713 0.9914 0.0049 -11.250 -0.7390 0.02567 0.02095 -0.0717 0.9726 0.0049 -11.000 -0.7073 0.02409 0.01927 -0.0751 0.9591 0.0049 -10.750 -0.6660 0.02256 0.01763 -0.0804 0.9492 0.0049 -10.500 -0.6148 0.02100 0.01595 -0.0878 0.9402 0.0051 -10.250 -0.5628 0.01967 0.01450 -0.0952 0.9220 0.0051 -10.000 -0.5328 0.01873 0.01337 -0.0978 0.8932 0.0053 -9.750 -0.5213 0.01791 0.01239 -0.0964 0.8677 0.0055 -9.250 -0.5011 0.01651 0.01075 -0.0928 0.8324 0.0056 -9.000 -0.4887 0.01594 0.01010 -0.0911 0.8188 0.0058 -8.750 -0.4901 0.01483 0.00888 -0.0877 0.8051 0.0063 -8.500 -0.4842 0.01423 0.00820 -0.0848 0.7933 0.0065 -8.250 -0.4755 0.01387 0.00777 -0.0819 0.7825 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0.6411 0.5549 -3.250 -0.0323 0.00699 0.00210 -0.0692 0.6345 0.5606 -3.000 -0.0037 0.00711 0.00215 -0.0693 0.6282 0.5675 -2.750 0.0248 0.00720 0.00224 -0.0695 0.6214 0.5761 -2.500 0.0530 0.00736 0.00233 -0.0695 0.6147 0.5826 -2.250 0.0821 0.00737 0.00230 -0.0699 0.6090 0.5841 -2.000 0.1107 0.00740 0.00226 -0.0701 0.6033 0.5851 -1.750 0.1389 0.00737 0.00218 -0.0703 0.5978 0.5869 -1.500 0.1677 0.00734 0.00214 -0.0707 0.5920 0.5883 -1.250 0.1961 0.00735 0.00211 -0.0709 0.5863 0.5895 -1.000 0.2246 0.00737 0.00210 -0.0711 0.5812 0.5908 -0.750 0.2533 0.00738 0.00209 -0.0714 0.5759 0.5922 -0.500 0.2816 0.00742 0.00209 -0.0716 0.5706 0.5936 -0.250 0.3101 0.00745 0.00209 -0.0719 0.5658 0.5950 0.000 0.3388 0.00747 0.00209 -0.0722 0.5610 0.5964 0.250 0.3670 0.00751 0.00209 -0.0724 0.5560 0.5976 0.500 0.3953 0.00756 0.00211 -0.0726 0.5513 0.5989 0.750 0.4241 0.00758 0.00212 -0.0729 0.5467 0.6000 1.500 0.5086 0.00766 0.00217 -0.0735 0.5338 0.6046 1.750 0.5369 0.00769 0.00221 -0.0738 0.5296 0.6061 2.000 0.5648 0.00774 0.00226 -0.0739 0.5253 0.6075 2.250 0.5925 0.00781 0.00231 -0.0741 0.5210 0.6090 2.500 0.6210 0.00784 0.00236 -0.0744 0.5168 0.6106 2.750 0.6489 0.00789 0.00241 -0.0745 0.5125 0.6121 3.000 0.6764 0.00798 0.00248 -0.0746 0.5083 0.6136 3.250 0.7043 0.00804 0.00255 -0.0748 0.5047 0.6151 3.500 0.7325 0.00809 0.00261 -0.0750 0.5004 0.6163 3.750 0.7598 0.00814 0.00267 -0.0751 0.4955 0.6183 4.000 0.7866 0.00821 0.00275 -0.0751 0.4904 0.6204 4.250 0.8145 0.00824 0.00283 -0.0753 0.4855 0.6224 4.500 0.8414 0.00832 0.00291 -0.0753 0.4798 0.6242 4.750 0.8681 0.00841 0.00301 -0.0752 0.4739 0.6261 5.000 0.8953 0.00848 0.00310 -0.0753 0.4675 0.6280 5.250 0.9213 0.00860 0.00321 -0.0751 0.4617 0.6299 5.500 0.9485 0.00867 0.00331 -0.0752 0.4562 0.6316 5.750 0.9748 0.00876 0.00341 -0.0751 0.4497 0.6336 6.000 1.0005 0.00885 0.00353 -0.0749 0.4431 0.6361 6.250 1.0264 0.00895 0.00366 -0.0747 0.4349 0.6384 6.500 1.0516 0.00907 0.00380 -0.0744 0.4267 0.6408 6.750 1.0762 0.00922 0.00395 -0.0741 0.4171 0.6434 7.000 1.1007 0.00937 0.00411 -0.0737 0.4057 0.6459 7.250 1.1241 0.00957 0.00429 -0.0731 0.3932 0.6481 7.500 1.1459 0.00979 0.00449 -0.0722 0.3775 0.6511 7.750 1.1654 0.01009 0.00475 -0.0709 0.3574 0.6540 8.000 1.1825 0.01049 0.00506 -0.0692 0.3303 0.6569 8.250 1.1929 0.01103 0.00545 -0.0663 0.2982 0.6599 8.500 1.2029 0.01153 0.00585 -0.0633 0.2786 0.6629 8.750 1.2155 0.01198 0.00627 -0.0608 0.2652 0.6661 9.000 1.2295 0.01240 0.00668 -0.0587 0.2522 0.6697 9.250 1.2440 0.01281 0.00709 -0.0566 0.2373 0.6736 9.500 1.2537 0.01340 0.00759 -0.0539 0.2138 0.6775 9.750 1.2593 0.01416 0.00824 -0.0507 0.1923 0.6816 10.000 1.2654 0.01490 0.00893 -0.0477 0.1741 0.6863 10.250 1.2720 0.01568 0.00967 -0.0449 0.1589 0.6916 10.500 1.2763 0.01661 0.01054 -0.0419 0.1421 0.6967 10.750 1.2818 0.01753 0.01145 -0.0394 0.1289 0.7026 11.000 1.2875 0.01852 0.01242 -0.0370 0.1172 0.7090 11.250 1.2925 0.01960 0.01350 -0.0346 0.1061 0.7157 11.500 1.2961 0.02083 0.01471 -0.0324 0.0947 0.7236 11.750 1.3000 0.02211 0.01599 -0.0303 0.0851 0.7322 12.000 1.3023 0.02356 0.01743 -0.0282 0.0744 0.7422 12.250 1.3089 0.02480 0.01873 -0.0267 0.0686 0.7541 12.500 1.3110 0.02638 0.02033 -0.0249 0.0608 0.7680 12.750 1.3143 0.02793 0.02194 -0.0234 0.0539 0.7856 13.000 1.3173 0.02951 0.02361 -0.0219 0.0481 0.8103 13.250 1.3178 0.03112 0.02538 -0.0201 0.0433 0.8580 13.500 1.3277 0.03275 0.02725 -0.0203 0.0379 1.0000 13.750 1.3293 0.03483 0.02931 -0.0194 0.0332 1.0000 14.000 1.3351 0.03661 0.03112 -0.0187 0.0307 1.0000 14.250 1.3375 0.03875 0.03327 -0.0181 0.0276 1.0000 14.500 1.3420 0.04077 0.03533 -0.0176 0.0251 1.0000 14.750 1.3449 0.04297 0.03755 -0.0171 0.0228 1.0000 15.000 1.3479 0.04524 0.03985 -0.0168 0.0207 1.0000 15.250 1.3522 0.04743 0.04209 -0.0166 0.0191 1.0000 15.500 1.3538 0.04996 0.04464 -0.0164 0.0173 1.0000 15.750 1.3567 0.05240 0.04714 -0.0164 0.0161 1.0000 16.000 1.3595 0.05489 0.04967 -0.0165 0.0147 1.0000 16.250 1.3608 0.05760 0.05243 -0.0166 0.0136 1.0000 16.500 1.3627 0.06033 0.05521 -0.0168 0.0125 1.0000 16.750 1.3651 0.06305 0.05798 -0.0172 0.0116 1.0000 17.000 1.3653 0.06606 0.06105 -0.0176 0.0107 1.0000 17.250 1.3643 0.06930 0.06434 -0.0181 0.0098 1.0000 17.500 1.3664 0.07223 0.06734 -0.0188 0.0092 1.0000 17.750 1.3667 0.07542 0.07060 -0.0195 0.0086 1.0000 18.000 1.3652 0.07888 0.07411 -0.0203 0.0079 1.0000 18.250 1.3627 0.08258 0.07788 -0.0213 0.0073 1.0000 18.500 1.3624 0.08603 0.08141 -0.0224 0.0070 1.0000 18.750 1.3620 0.08953 0.08496 -0.0235 0.0062 1.0000 19.000 1.3588 0.09351 0.08902 -0.0248 0.0060 1.0000 19.250 1.3506 0.09830 0.09390 -0.0265 0.0055 1.0000