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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.2831 0.09289 0.09134 -0.0280 1.0000 0.0123 -9.250 -0.2795 0.08999 0.08844 -0.0283 1.0000 0.0125 -9.000 -0.3792 0.09831 0.09667 -0.0235 1.0000 0.0121 -8.750 -0.3726 0.09530 0.09367 -0.0233 1.0000 0.0122 -8.500 -0.3669 0.09266 0.09104 -0.0240 1.0000 0.0124 -8.250 -0.3625 0.09012 0.08852 -0.0247 1.0000 0.0125 -8.000 -0.3620 0.08782 0.08625 -0.0246 1.0000 0.0127 -7.750 -0.3727 0.08641 0.08489 -0.0219 1.0000 0.0128 -7.500 -0.3529 0.08232 0.08080 -0.0280 0.9969 0.0132 -7.250 -0.3285 0.07776 0.07622 -0.0355 0.9943 0.0140 -7.000 -0.2907 0.07025 0.06866 -0.0515 0.9881 0.0150 -6.750 -0.2587 0.06408 0.06242 -0.0611 0.9844 0.0151 -6.500 -0.2394 0.05858 0.05688 -0.0660 0.9772 0.0153 -6.250 -0.2165 0.05579 0.05405 -0.0688 0.9717 0.0156 -6.000 -0.1944 0.05292 0.05114 -0.0716 0.9621 0.0159 -5.750 -0.1705 0.04985 0.04799 -0.0746 0.9532 0.0165 -5.500 -0.1340 0.04479 0.04269 -0.0800 0.9435 0.0186 -5.250 -0.1076 0.04056 0.03828 -0.0822 0.9337 0.0187 -5.000 -0.0874 0.03524 0.03275 -0.0842 0.9244 0.0190 -4.750 -0.0662 0.03358 0.03101 -0.0845 0.9147 0.0193 -4.500 -0.0428 0.03191 0.02924 -0.0849 0.9060 0.0197 -4.250 -0.0179 0.03007 0.02728 -0.0854 0.8988 0.0206 -4.000 0.0162 0.02769 0.02457 -0.0852 0.8923 0.0230 -3.750 0.0425 0.02506 0.02170 -0.0852 0.8854 0.0230 -3.500 0.0649 0.02115 0.01756 -0.0858 0.8785 0.0238 -3.250 0.0902 0.02011 0.01642 -0.0859 0.8704 0.0242 -3.000 0.1163 0.01917 0.01538 -0.0859 0.8622 0.0252 -2.750 0.1460 0.01885 0.01485 -0.0851 0.8536 0.0283 -2.500 0.1736 0.01762 0.01339 -0.0848 0.8447 0.0285 -2.250 0.1989 0.01422 0.00962 -0.0847 0.8357 0.0294 -2.000 0.2255 0.01345 0.00880 -0.0846 0.8242 0.0301 -1.750 0.2523 0.01292 0.00819 -0.0845 0.8110 0.0311 -1.500 0.2795 0.01237 0.00751 -0.0843 0.7953 0.0331 -1.250 0.3074 0.01295 0.00794 -0.0837 0.7746 0.0355 -1.000 0.3332 0.01091 0.00559 -0.0834 0.7478 0.0374 -0.750 0.3589 0.01054 0.00507 -0.0830 0.7073 0.0385 -0.500 0.3846 0.01034 0.00467 -0.0825 0.6662 0.0400 -0.250 0.4110 0.01019 0.00436 -0.0821 0.6369 0.0422 0.000 0.4379 0.00911 0.00306 -0.0813 0.6144 0.0334 0.250 0.4644 0.00877 0.00261 -0.0810 0.5917 0.0332 0.500 0.4910 0.00859 0.00233 -0.0807 0.5682 0.0334 0.750 0.5177 0.00847 0.00211 -0.0804 0.5419 0.0336 1.000 0.5442 0.00842 0.00194 -0.0801 0.5112 0.0338 1.250 0.5704 0.00847 0.00184 -0.0798 0.4752 0.0342 1.500 0.5962 0.00862 0.00180 -0.0795 0.4324 0.0349 1.750 0.6223 0.00875 0.00176 -0.0792 0.3980 0.0352 2.000 0.6491 0.00882 0.00175 -0.0790 0.3785 0.0357 2.250 0.6761 0.00882 0.00167 -0.0788 0.3645 0.0377 2.500 0.7032 0.00889 0.00169 -0.0787 0.3525 0.0399 2.750 0.7302 0.00899 0.00174 -0.0786 0.3405 0.0425 3.000 0.7572 0.00908 0.00181 -0.0784 0.3291 0.0524 3.250 0.7822 0.00733 0.00209 -0.0784 0.3221 1.0000 3.500 0.8090 0.00748 0.00218 -0.0782 0.3139 1.0000 3.750 0.8361 0.00761 0.00227 -0.0781 0.3060 1.0000 4.000 0.8628 0.00778 0.00239 -0.0779 0.2969 1.0000 4.250 0.8898 0.00791 0.00250 -0.0778 0.2883 1.0000 4.500 0.9164 0.00809 0.00262 -0.0776 0.2751 1.0000 4.750 0.9425 0.00832 0.00277 -0.0774 0.2548 1.0000 5.000 0.9665 0.00881 0.00300 -0.0768 0.2053 1.0000 5.250 0.9868 0.00977 0.00354 -0.0758 0.1305 1.0000 5.500 1.0054 0.01101 0.00430 -0.0745 0.0431 1.0000 5.750 1.0310 0.01130 0.00460 -0.0742 0.0404 1.0000 6.000 1.0561 0.01164 0.00494 -0.0738 0.0378 1.0000 6.250 1.0810 0.01202 0.00533 -0.0733 0.0352 1.0000 6.500 1.1053 0.01246 0.00583 -0.0727 0.0334 1.0000 6.750 1.1306 0.01274 0.00615 -0.0724 0.0329 1.0000 7.000 1.1554 0.01307 0.00650 -0.0720 0.0321 1.0000 7.250 1.1799 0.01342 0.00689 -0.0715 0.0309 1.0000 7.500 1.2041 0.01381 0.00731 -0.0710 0.0297 1.0000 7.750 1.2276 0.01425 0.00778 -0.0705 0.0285 1.0000 8.000 1.2494 0.01488 0.00845 -0.0696 0.0269 1.0000 8.250 1.2692 0.01570 0.00937 -0.0684 0.0254 1.0000 8.500 1.2936 0.01598 0.00968 -0.0680 0.0249 1.0000 8.750 1.3172 0.01632 0.01005 -0.0675 0.0239 1.0000 9.000 1.3405 0.01667 0.01042 -0.0670 0.0228 1.0000 9.250 1.3636 0.01703 0.01079 -0.0664 0.0216 1.0000 9.500 1.3833 0.01770 0.01149 -0.0653 0.0204 1.0000 9.750 1.4009 0.01854 0.01241 -0.0639 0.0193 1.0000 10.000 1.4240 0.01881 0.01272 -0.0634 0.0186 1.0000 10.250 1.4465 0.01913 0.01306 -0.0628 0.0176 1.0000 10.500 1.4692 0.01941 0.01335 -0.0622 0.0166 1.0000 10.750 1.4877 0.02003 0.01397 -0.0611 0.0155 1.0000 11.000 1.5029 0.02088 0.01490 -0.0594 0.0147 1.0000 11.250 1.5221 0.02136 0.01544 -0.0583 0.0141 1.0000 11.500 1.5398 0.02190 0.01602 -0.0570 0.0134 1.0000 11.750 1.5556 0.02243 0.01659 -0.0554 0.0128 1.0000 12.000 1.5675 0.02318 0.01737 -0.0533 0.0121 1.0000 12.250 1.5665 0.02476 0.01906 -0.0495 0.0114 1.0000 12.500 1.5793 0.02551 0.01988 -0.0477 0.0112 1.0000 12.750 1.5903 0.02640 0.02086 -0.0459 0.0108 1.0000 13.000 1.5998 0.02743 0.02197 -0.0441 0.0104 1.0000 13.250 1.6081 0.02861 0.02322 -0.0423 0.0100 1.0000 13.500 1.6152 0.02993 0.02463 -0.0406 0.0097 1.0000 13.750 1.6199 0.03152 0.02628 -0.0390 0.0093 1.0000 14.000 1.6196 0.03365 0.02851 -0.0372 0.0090 1.0000 14.250 1.6113 0.03669 0.03168 -0.0355 0.0087 1.0000 14.500 1.6009 0.04025 0.03539 -0.0343 0.0085 1.0000 14.750 1.6022 0.04278 0.03804 -0.0339 0.0084 1.0000 15.000 1.6007 0.04581 0.04119 -0.0338 0.0083 1.0000 15.250 1.5974 0.04925 0.04476 -0.0341 0.0082 1.0000 15.500 1.5927 0.05305 0.04870 -0.0347 0.0081 1.0000 15.750 1.5860 0.05730 0.05307 -0.0357 0.0079 1.0000 16.000 1.5773 0.06193 0.05784 -0.0369 0.0078 1.0000 16.250 1.5676 0.06685 0.06289 -0.0384 0.0077 1.0000 16.500 1.5562 0.07217 0.06833 -0.0401 0.0076 1.0000 16.750 1.5441 0.07766 0.07395 -0.0420 0.0076 1.0000 17.000 1.5311 0.08341 0.07981 -0.0440 0.0075 1.0000 17.250 1.5175 0.08936 0.08588 -0.0463 0.0074 1.0000 17.500 1.5034 0.09543 0.09207 -0.0486 0.0073 1.0000 17.750 1.4895 0.10154 0.09829 -0.0510 0.0073 1.0000