XFOIL Version 6.96 Calculated polar for: GOE 277 (DAIMLER VIII) 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.3559 0.08950 0.08796 -0.0257 1.0000 0.0148 -8.000 -0.3587 0.08657 0.08505 -0.0262 1.0000 0.0148 -7.750 -0.3668 0.08415 0.08268 -0.0253 0.9999 0.0148 -7.500 -0.3448 0.07816 0.07667 -0.0341 0.9965 0.0149 -7.250 -0.3272 0.07249 0.07100 -0.0404 0.9941 0.0152 -7.000 -0.3042 0.06945 0.06794 -0.0447 0.9904 0.0156 -6.750 -0.2776 0.06580 0.06427 -0.0507 0.9861 0.0161 -6.500 -0.2502 0.06155 0.05997 -0.0574 0.9798 0.0171 -6.250 -0.2098 0.05307 0.05133 -0.0704 0.9709 0.0187 -6.000 -0.1843 0.04711 0.04523 -0.0755 0.9599 0.0188 -5.750 -0.1662 0.04032 0.03826 -0.0798 0.9487 0.0194 -5.500 -0.1455 0.03933 0.03722 -0.0800 0.9381 0.0198 -5.000 -0.0897 0.03382 0.03135 -0.0822 0.9155 0.0236 -4.750 -0.0637 0.02923 0.02642 -0.0833 0.9035 0.0237 -4.500 -0.0433 0.02288 0.01963 -0.0848 0.8907 0.0247 -4.250 -0.0185 0.02234 0.01902 -0.0848 0.8752 0.0254 -4.000 0.0068 0.02157 0.01812 -0.0847 0.8565 0.0264 -3.750 0.0362 0.02210 0.01844 -0.0838 0.8326 0.0300 -2.500 -0.0132 0.02492 0.02093 -0.0603 0.7235 0.0282 -2.250 0.1968 0.01169 0.00606 -0.0832 0.6993 0.0310 -2.000 0.2248 0.01116 0.00540 -0.0831 0.6843 0.0308 -1.750 0.2524 0.01015 0.00426 -0.0831 0.6689 0.0315 -1.500 0.2801 0.00963 0.00364 -0.0830 0.6511 0.0320 -1.250 0.3077 0.00930 0.00321 -0.0829 0.6304 0.0324 -1.000 0.3354 0.00904 0.00286 -0.0828 0.6065 0.0328 -0.750 0.3629 0.00886 0.00256 -0.0827 0.5820 0.0332 -0.500 0.3905 0.00872 0.00231 -0.0826 0.5586 0.0336 -0.250 0.4182 0.00861 0.00211 -0.0825 0.5380 0.0341 0.000 0.4460 0.00855 0.00197 -0.0825 0.5190 0.0351 0.250 0.4739 0.00850 0.00184 -0.0824 0.5012 0.0361 0.500 0.5017 0.00847 0.00173 -0.0824 0.4832 0.0372 0.750 0.5295 0.00848 0.00166 -0.0824 0.4646 0.0382 1.000 0.5573 0.00852 0.00162 -0.0824 0.4445 0.0389 1.250 0.5850 0.00854 0.00153 -0.0823 0.4244 0.0408 1.500 0.6128 0.00859 0.00150 -0.0823 0.4056 0.0447 1.750 0.6404 0.00866 0.00151 -0.0823 0.3887 0.0531 2.000 0.6630 0.00672 0.00174 -0.0818 0.3747 1.0000 2.250 0.6905 0.00689 0.00181 -0.0817 0.3614 1.0000 2.500 0.7182 0.00704 0.00188 -0.0817 0.3513 1.0000 2.750 0.7459 0.00717 0.00197 -0.0817 0.3440 1.0000 3.000 0.7735 0.00733 0.00206 -0.0817 0.3368 1.0000 3.250 0.8012 0.00745 0.00215 -0.0816 0.3308 1.0000 3.500 0.8289 0.00759 0.00226 -0.0816 0.3252 1.0000 3.750 0.8562 0.00776 0.00238 -0.0816 0.3190 1.0000 4.000 0.8841 0.00786 0.00248 -0.0816 0.3151 1.0000 4.250 0.9116 0.00799 0.00260 -0.0816 0.3108 1.0000 4.500 0.9389 0.00816 0.00275 -0.0815 0.3060 1.0000 4.750 0.9665 0.00828 0.00288 -0.0815 0.3021 1.0000 5.000 0.9938 0.00842 0.00299 -0.0815 0.2944 1.0000 5.250 1.0210 0.00858 0.00315 -0.0814 0.2881 1.0000 5.500 1.0483 0.00871 0.00327 -0.0814 0.2809 1.0000 5.750 1.0753 0.00888 0.00342 -0.0813 0.2732 1.0000 6.000 1.1023 0.00904 0.00357 -0.0812 0.2643 1.0000 6.250 1.1292 0.00921 0.00373 -0.0812 0.2544 1.0000 6.500 1.1555 0.00945 0.00392 -0.0810 0.2381 1.0000 6.750 1.1807 0.00981 0.00416 -0.0807 0.2120 1.0000 7.000 1.2008 0.01082 0.00477 -0.0798 0.1453 1.0000 7.250 1.2198 0.01195 0.00556 -0.0787 0.0901 1.0000 7.500 1.2418 0.01270 0.00613 -0.0780 0.0610 1.0000 7.750 1.2595 0.01394 0.00710 -0.0766 0.0183 1.0000 8.000 1.2824 0.01452 0.00771 -0.0759 0.0152 1.0000 8.250 1.3061 0.01495 0.00819 -0.0754 0.0144 1.0000 8.500 1.3291 0.01545 0.00875 -0.0747 0.0134 1.0000 8.750 1.3509 0.01606 0.00940 -0.0739 0.0124 1.0000 9.000 1.3693 0.01700 0.01045 -0.0725 0.0113 1.0000 9.250 1.3916 0.01747 0.01096 -0.0718 0.0109 1.0000 9.500 1.4124 0.01806 0.01161 -0.0709 0.0104 1.0000 9.750 1.4321 0.01872 0.01233 -0.0698 0.0099 1.0000 10.000 1.4507 0.01943 0.01310 -0.0686 0.0095 1.0000 10.250 1.4677 0.02023 0.01396 -0.0672 0.0091 1.0000 10.500 1.4802 0.02132 0.01514 -0.0652 0.0087 1.0000 10.750 1.4804 0.02314 0.01711 -0.0614 0.0083 1.0000 11.000 1.4880 0.02411 0.01816 -0.0585 0.0082 1.0000 11.250 1.4987 0.02496 0.01907 -0.0563 0.0080 1.0000 11.500 1.5073 0.02598 0.02018 -0.0540 0.0078 1.0000 11.750 1.5152 0.02712 0.02140 -0.0519 0.0076 1.0000 12.000 1.5217 0.02843 0.02280 -0.0499 0.0073 1.0000 12.250 1.5265 0.02998 0.02443 -0.0480 0.0071 1.0000 12.500 1.5300 0.03175 0.02630 -0.0464 0.0070 1.0000 12.750 1.5328 0.03375 0.02838 -0.0450 0.0068 1.0000 13.000 1.5338 0.03608 0.03080 -0.0440 0.0067 1.0000 13.250 1.5343 0.03866 0.03348 -0.0434 0.0065 1.0000 13.500 1.5330 0.04165 0.03657 -0.0432 0.0064 1.0000 13.750 1.5295 0.04504 0.04005 -0.0433 0.0063 1.0000 14.000 1.5233 0.04891 0.04403 -0.0436 0.0062 1.0000 14.250 1.5131 0.05336 0.04858 -0.0441 0.0061 1.0000 14.500 1.5014 0.05808 0.05342 -0.0447 0.0060 1.0000 14.750 1.4880 0.06300 0.05845 -0.0452 0.0059 1.0000 15.000 1.4700 0.06830 0.06388 -0.0453 0.0058 1.0000 15.250 1.4658 0.07245 0.06814 -0.0464 0.0058 1.0000 15.500 1.4604 0.07675 0.07255 -0.0476 0.0058 1.0000 15.750 1.4549 0.08120 0.07711 -0.0490 0.0057 1.0000 16.000 1.4486 0.08582 0.08184 -0.0504 0.0057 1.0000 16.250 1.4418 0.09056 0.08668 -0.0519 0.0057 1.0000 16.500 1.4344 0.09541 0.09164 -0.0535 0.0056 1.0000 16.750 1.4271 0.10037 0.09671 -0.0552 0.0056 1.0000 17.000 1.4195 0.10544 0.10189 -0.0571 0.0055 1.0000 17.250 1.4115 0.11062 0.10718 -0.0590 0.0055 1.0000 17.500 1.4032 0.11592 0.11259 -0.0612 0.0055 1.0000 17.750 1.3947 0.12136 0.11815 -0.0635 0.0054 1.0000 18.000 1.3861 0.12694 0.12384 -0.0660 0.0054 1.0000 18.250 1.3770 0.13267 0.12969 -0.0687 0.0053 1.0000 18.500 1.3679 0.13851 0.13564 -0.0716 0.0053 1.0000 18.750 1.3584 0.14456 0.14181 -0.0747 0.0053 1.0000 19.000 1.3482 0.15092 0.14829 -0.0782 0.0053 1.0000 19.250 1.3384 0.15745 0.15493 -0.0819 0.0052 1.0000