XFOIL Version 6.96 Calculated polar for: GOE 278 (DAIMLER IX) 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3679 0.09570 0.09407 -0.0252 1.0000 0.0058 -8.750 -0.3660 0.09223 0.09061 -0.0265 1.0000 0.0060 -8.500 -0.3635 0.08824 0.08665 -0.0286 0.9978 0.0063 -8.250 -0.3562 0.08173 0.08014 -0.0354 0.9867 0.0067 -8.000 -0.3402 0.07675 0.07515 -0.0424 0.9758 0.0069 -7.750 -0.3213 0.07319 0.07156 -0.0477 0.9633 0.0071 -7.500 -0.3035 0.06983 0.06816 -0.0522 0.9483 0.0073 -7.250 -0.2862 0.06636 0.06464 -0.0565 0.9341 0.0076 -7.000 -0.2677 0.06195 0.06015 -0.0618 0.9220 0.0081 -6.750 -0.2462 0.05233 0.05036 -0.0727 0.9102 0.0092 -6.500 -0.2234 0.04958 0.04752 -0.0756 0.9010 0.0094 -6.250 -0.2000 0.04685 0.04469 -0.0781 0.8917 0.0096 -6.000 -0.1754 0.04368 0.04141 -0.0809 0.8829 0.0101 -5.750 -0.1481 0.03543 0.03281 -0.0862 0.8755 0.0119 -5.500 -0.1228 0.03375 0.03102 -0.0871 0.8675 0.0121 -5.250 -0.0975 0.03198 0.02912 -0.0879 0.8588 0.0125 -5.000 -0.0703 0.02450 0.02112 -0.0897 0.8505 0.0150 -4.750 -0.0447 0.02359 0.02009 -0.0898 0.8391 0.0152 -4.500 -0.0189 0.02266 0.01903 -0.0899 0.8263 0.0155 -4.250 0.0071 0.02160 0.01781 -0.0899 0.8134 0.0159 -4.000 0.0333 0.01523 0.01073 -0.0896 0.8035 0.0188 -3.750 0.0598 0.01456 0.00992 -0.0895 0.7905 0.0191 -3.500 0.0865 0.01431 0.00956 -0.0894 0.7731 0.0194 -3.250 0.1130 0.01407 0.00918 -0.0892 0.7489 0.0198 -3.000 0.1389 0.01356 0.00844 -0.0889 0.7133 0.0202 -2.750 0.1647 0.01279 0.00738 -0.0885 0.6764 0.0206 -2.500 0.1910 0.01198 0.00629 -0.0881 0.6473 0.0212 -2.250 0.2177 0.01133 0.00542 -0.0879 0.6257 0.0218 -2.000 0.2447 0.01086 0.00478 -0.0877 0.6083 0.0224 -1.750 0.2719 0.01050 0.00428 -0.0875 0.5924 0.0228 -1.500 0.2991 0.01026 0.00392 -0.0873 0.5759 0.0231 -1.250 0.3263 0.01011 0.00366 -0.0872 0.5580 0.0233 -1.000 0.3534 0.00992 0.00337 -0.0870 0.5387 0.0235 -0.750 0.3800 0.00941 0.00275 -0.0868 0.5176 0.0239 -0.500 0.4067 0.00920 0.00243 -0.0866 0.4939 0.0241 -0.250 0.4333 0.00910 0.00222 -0.0864 0.4675 0.0244 0.000 0.4599 0.00910 0.00210 -0.0862 0.4386 0.0249 0.250 0.4864 0.00913 0.00202 -0.0860 0.4101 0.0253 0.500 0.5132 0.00913 0.00192 -0.0859 0.3881 0.0256 0.750 0.5403 0.00912 0.00184 -0.0857 0.3727 0.0259 1.000 0.5672 0.00915 0.00179 -0.0856 0.3543 0.0265 1.250 0.5940 0.00922 0.00177 -0.0854 0.3353 0.0271 1.500 0.6212 0.00926 0.00176 -0.0853 0.3230 0.0278 1.750 0.6485 0.00930 0.00176 -0.0852 0.3157 0.0284 2.000 0.6760 0.00931 0.00176 -0.0852 0.3106 0.0289 2.250 0.7034 0.00935 0.00179 -0.0851 0.3046 0.0293 2.500 0.7306 0.00942 0.00183 -0.0850 0.2947 0.0296 2.750 0.7577 0.00949 0.00187 -0.0849 0.2868 0.0304 3.000 0.7850 0.00954 0.00191 -0.0848 0.2798 0.0319 3.250 0.8119 0.00965 0.00198 -0.0847 0.2696 0.0337 3.500 0.8388 0.00976 0.00207 -0.0846 0.2580 0.0369 3.750 0.8654 0.00975 0.00223 -0.0845 0.2430 0.1957 4.250 0.9122 0.00893 0.00280 -0.0835 0.1775 1.0000 4.500 0.9364 0.00940 0.00310 -0.0830 0.1462 1.0000 4.750 0.9582 0.01019 0.00355 -0.0822 0.0837 1.0000 5.000 0.9810 0.01085 0.00401 -0.0815 0.0408 1.0000 5.250 1.0067 0.01113 0.00425 -0.0812 0.0365 1.0000 5.500 1.0325 0.01138 0.00451 -0.0809 0.0337 1.0000 5.750 1.0582 0.01163 0.00476 -0.0806 0.0325 1.0000 6.000 1.0839 0.01187 0.00501 -0.0803 0.0321 1.0000 6.250 1.1095 0.01212 0.00528 -0.0800 0.0317 1.0000 6.500 1.1348 0.01238 0.00558 -0.0796 0.0314 1.0000 6.750 1.1600 0.01266 0.00588 -0.0793 0.0309 1.0000 7.000 1.1850 0.01295 0.00619 -0.0789 0.0303 1.0000 7.250 1.2098 0.01325 0.00651 -0.0785 0.0295 1.0000 7.500 1.2343 0.01356 0.00686 -0.0781 0.0284 1.0000 7.750 1.2584 0.01391 0.00722 -0.0777 0.0272 1.0000 8.000 1.2821 0.01430 0.00763 -0.0771 0.0259 1.0000 8.250 1.3049 0.01478 0.00816 -0.0765 0.0245 1.0000 8.500 1.3286 0.01513 0.00854 -0.0759 0.0239 1.0000 8.750 1.3528 0.01540 0.00884 -0.0755 0.0234 1.0000 9.000 1.3767 0.01568 0.00915 -0.0751 0.0225 1.0000 9.250 1.4001 0.01600 0.00949 -0.0746 0.0212 1.0000 9.500 1.4230 0.01635 0.00987 -0.0740 0.0196 1.0000 9.750 1.4450 0.01678 0.01028 -0.0733 0.0177 1.0000 10.000 1.4669 0.01718 0.01071 -0.0726 0.0160 1.0000 10.250 1.4879 0.01765 0.01114 -0.0717 0.0135 1.0000 10.500 1.5080 0.01817 0.01170 -0.0708 0.0118 1.0000 10.750 1.5270 0.01876 0.01231 -0.0696 0.0103 1.0000 11.000 1.5455 0.01936 0.01296 -0.0684 0.0093 1.0000 11.250 1.5631 0.01998 0.01363 -0.0671 0.0085 1.0000 11.500 1.5790 0.02068 0.01438 -0.0655 0.0078 1.0000 11.750 1.5918 0.02145 0.01520 -0.0634 0.0070 1.0000 12.000 1.6047 0.02214 0.01596 -0.0614 0.0067 1.0000 12.250 1.6163 0.02290 0.01680 -0.0592 0.0063 1.0000 12.500 1.6265 0.02377 0.01774 -0.0570 0.0059 1.0000 12.750 1.6356 0.02475 0.01879 -0.0548 0.0056 1.0000 13.000 1.6430 0.02588 0.01999 -0.0525 0.0053 1.0000 13.250 1.6485 0.02720 0.02141 -0.0503 0.0050 1.0000 13.500 1.6558 0.02845 0.02275 -0.0484 0.0049 1.0000 13.750 1.6620 0.02984 0.02423 -0.0466 0.0048 1.0000 14.000 1.6670 0.03141 0.02590 -0.0449 0.0046 1.0000 14.250 1.6708 0.03315 0.02774 -0.0433 0.0045 1.0000 14.500 1.6733 0.03510 0.02979 -0.0420 0.0043 1.0000 14.750 1.6746 0.03729 0.03209 -0.0408 0.0042 1.0000 15.000 1.6742 0.03976 0.03466 -0.0398 0.0041 1.0000 15.250 1.6723 0.04257 0.03758 -0.0392 0.0040 1.0000 15.500 1.6690 0.04572 0.04084 -0.0390 0.0039 1.0000 15.750 1.6637 0.04932 0.04456 -0.0391 0.0038 1.0000 16.000 1.6565 0.05340 0.04877 -0.0397 0.0037 1.0000 16.250 1.6471 0.05796 0.05346 -0.0407 0.0036 1.0000 16.500 1.6351 0.06305 0.05868 -0.0420 0.0035 1.0000 16.750 1.6214 0.06860 0.06436 -0.0436 0.0035 1.0000 17.000 1.6049 0.07471 0.07061 -0.0456 0.0034 1.0000 17.250 1.5896 0.08077 0.07680 -0.0477 0.0034 1.0000 17.500 1.5743 0.08694 0.08310 -0.0499 0.0034 1.0000 17.750 1.5581 0.09329 0.08958 -0.0522 0.0034 1.0000 18.000 1.5419 0.09973 0.09613 -0.0546 0.0034 1.0000 18.250 1.5258 0.10623 0.10276 -0.0572 0.0033 1.0000