XFOIL Version 6.96 Calculated polar for: Gottingen 765 airfoil (recovered). Thick: .144 L 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 ------ -------- --------- --------- -------- -------- -------- -13.250 -0.7206 0.07910 0.07340 -0.0354 1.0000 0.0466 -13.000 -0.7783 0.06720 0.06123 -0.0436 1.0000 0.0460 -12.750 -0.8171 0.06064 0.05441 -0.0454 1.0000 0.0458 -12.500 -0.8477 0.05591 0.04940 -0.0445 1.0000 0.0459 -12.250 -0.8720 0.05216 0.04536 -0.0422 1.0000 0.0462 -12.000 -0.8925 0.04890 0.04177 -0.0388 1.0000 0.0466 -11.750 -0.9085 0.04604 0.03855 -0.0348 1.0000 0.0471 -11.500 -0.9119 0.04394 0.03625 -0.0316 1.0000 0.0478 -11.250 -0.9063 0.04242 0.03465 -0.0292 1.0000 0.0483 -11.000 -0.9002 0.04103 0.03318 -0.0266 1.0000 0.0492 -10.750 -0.8937 0.03960 0.03162 -0.0241 1.0000 0.0502 -10.500 -0.8863 0.03798 0.02979 -0.0216 1.0000 0.0515 -10.250 -0.8788 0.03624 0.02773 -0.0190 1.0000 0.0532 -10.000 -0.8660 0.03474 0.02606 -0.0171 1.0000 0.0545 -9.750 -0.8501 0.03368 0.02499 -0.0156 1.0000 0.0558 -9.500 -0.8344 0.03254 0.02377 -0.0140 1.0000 0.0574 -9.250 -0.8185 0.03134 0.02240 -0.0123 1.0000 0.0593 -9.000 -0.8024 0.03016 0.02102 -0.0107 1.0000 0.0616 -8.750 -0.7865 0.02936 0.02030 -0.0090 1.0000 0.0634 -8.500 -0.7736 0.02861 0.01953 -0.0068 1.0000 0.0655 -8.250 -0.7436 0.02749 0.01818 -0.0078 0.9825 0.0690 -8.000 -0.7083 0.02646 0.01719 -0.0099 0.9651 0.0724 -7.750 -0.6719 0.02549 0.01609 -0.0120 0.9504 0.0771 -7.500 -0.6371 0.02455 0.01512 -0.0138 0.9367 0.0817 -7.250 -0.6040 0.02377 0.01425 -0.0151 0.9230 0.0872 -7.000 -0.5752 0.02303 0.01348 -0.0154 0.9089 0.0925 -6.750 -0.5492 0.02246 0.01283 -0.0151 0.8948 0.0989 -6.500 -0.5255 0.02188 0.01224 -0.0144 0.8814 0.1051 -6.250 -0.5018 0.02141 0.01167 -0.0135 0.8692 0.1129 -6.000 -0.4802 0.02091 0.01121 -0.0123 0.8572 0.1209 -5.750 -0.4582 0.02047 0.01074 -0.0111 0.8451 0.1305 -5.500 -0.4360 0.02008 0.01030 -0.0099 0.8346 0.1417 -5.250 -0.4146 0.01965 0.00993 -0.0086 0.8235 0.1541 -5.000 -0.3927 0.01926 0.00957 -0.0074 0.8131 0.1687 -4.500 -0.3484 0.01853 0.00892 -0.0050 0.7928 0.2067 -4.250 -0.3260 0.01816 0.00861 -0.0037 0.7839 0.2308 -4.000 -0.3035 0.01781 0.00837 -0.0027 0.7731 0.2595 -3.750 -0.2809 0.01743 0.00807 -0.0015 0.7647 0.2935 -3.500 -0.2585 0.01704 0.00785 -0.0004 0.7539 0.3343 -3.250 -0.2365 0.01654 0.00756 0.0009 0.7456 0.3886 -3.000 -0.2152 0.01584 0.00737 0.0022 0.7351 0.4836 -2.750 -0.1075 0.01587 0.00849 -0.0108 0.7266 0.7539 -2.500 -0.0719 0.01637 0.00895 -0.0110 0.7155 0.8002 -2.250 -0.0478 0.01667 0.00912 -0.0094 0.7064 0.8297 -2.000 -0.0174 0.01709 0.00942 -0.0090 0.6957 0.8504 -1.750 0.0141 0.01746 0.00966 -0.0089 0.6861 0.8678 -1.500 0.0463 0.01778 0.00986 -0.0090 0.6758 0.8828 -1.250 0.0766 0.01805 0.01002 -0.0090 0.6657 0.8965 -1.000 0.1151 0.01832 0.01016 -0.0105 0.6556 0.9081 -0.750 0.1572 0.01860 0.01035 -0.0127 0.6442 0.9203 -0.500 0.1994 0.01881 0.01043 -0.0150 0.6342 0.9333 -0.250 0.2407 0.01896 0.01051 -0.0173 0.6221 0.9455 0.000 0.2779 0.01903 0.01049 -0.0190 0.6110 0.9564 0.250 0.3190 0.01887 0.01022 -0.0216 0.5999 0.9625 0.500 0.3490 0.01883 0.01013 -0.0222 0.5880 0.9682 0.750 0.3792 0.01872 0.00994 -0.0228 0.5777 0.9721 1.000 0.4111 0.01858 0.00975 -0.0238 0.5659 0.9758 1.250 0.4404 0.01853 0.00964 -0.0242 0.5544 0.9799 1.500 0.4697 0.01846 0.00948 -0.0247 0.5443 0.9835 1.750 0.5013 0.01834 0.00935 -0.0257 0.5318 0.9867 2.000 0.5314 0.01827 0.00924 -0.0264 0.5207 0.9901 2.250 0.5607 0.01826 0.00915 -0.0268 0.5100 0.9934 2.500 0.5916 0.01816 0.00906 -0.0278 0.4978 0.9962 2.750 0.6219 0.01812 0.00897 -0.0285 0.4872 0.9991 3.000 0.6464 0.01817 0.00899 -0.0281 0.4763 1.0000 3.250 0.6680 0.01829 0.00911 -0.0271 0.4659 1.0000 3.500 0.6895 0.01841 0.00917 -0.0261 0.4567 1.0000 3.750 0.7110 0.01856 0.00935 -0.0251 0.4458 1.0000 4.000 0.7324 0.01872 0.00945 -0.0240 0.4369 1.0000 4.250 0.7537 0.01889 0.00967 -0.0230 0.4264 1.0000 4.500 0.7749 0.01909 0.00984 -0.0220 0.4171 1.0000 4.750 0.7959 0.01929 0.01006 -0.0209 0.4073 1.0000 5.000 0.8168 0.01952 0.01031 -0.0198 0.3978 1.0000 5.250 0.8375 0.01975 0.01053 -0.0187 0.3885 1.0000 5.500 0.8580 0.02001 0.01083 -0.0175 0.3788 1.0000 5.750 0.8782 0.02027 0.01107 -0.0163 0.3699 1.0000 6.000 0.8981 0.02057 0.01144 -0.0151 0.3598 1.0000 6.250 0.9178 0.02086 0.01169 -0.0138 0.3511 1.0000 6.500 0.9369 0.02119 0.01212 -0.0125 0.3408 1.0000 6.750 0.9557 0.02153 0.01246 -0.0111 0.3317 1.0000 7.000 0.9740 0.02188 0.01287 -0.0097 0.3217 1.0000 7.250 0.9917 0.02226 0.01330 -0.0082 0.3119 1.0000 7.500 1.0087 0.02265 0.01369 -0.0066 0.3022 1.0000 7.750 1.0251 0.02308 0.01421 -0.0049 0.2916 1.0000 8.000 1.0406 0.02352 0.01465 -0.0031 0.2821 1.0000 8.250 1.0550 0.02399 0.01520 -0.0011 0.2715 1.0000 8.500 1.0686 0.02450 0.01577 0.0009 0.2612 1.0000 8.750 1.0805 0.02504 0.01628 0.0032 0.2516 1.0000 9.000 1.0915 0.02561 0.01696 0.0056 0.2407 1.0000 9.250 1.1008 0.02624 0.01762 0.0082 0.2308 1.0000 9.500 1.1075 0.02691 0.01830 0.0111 0.2214 1.0000 9.750 1.1133 0.02762 0.01908 0.0142 0.2114 1.0000 10.000 1.1154 0.02840 0.01985 0.0177 0.2028 1.0000 10.250 1.1145 0.02919 0.02070 0.0216 0.1942 1.0000 10.500 1.1077 0.03003 0.02154 0.0262 0.1874 1.0000 10.750 1.1021 0.03100 0.02257 0.0303 0.1798 1.0000 11.000 1.0964 0.03217 0.02373 0.0338 0.1731 1.0000 11.250 1.0925 0.03348 0.02510 0.0368 0.1653 1.0000 11.500 1.0877 0.03498 0.02659 0.0394 0.1585 1.0000 11.750 1.0842 0.03660 0.02828 0.0417 0.1510 1.0000 12.000 1.0796 0.03843 0.03009 0.0436 0.1448 1.0000 12.250 1.0762 0.04036 0.03211 0.0452 0.1378 1.0000 12.500 1.0706 0.04254 0.03426 0.0466 0.1322 1.0000 12.750 1.0673 0.04475 0.03657 0.0477 0.1258 1.0000 13.000 1.0608 0.04729 0.03909 0.0486 0.1208 1.0000 13.250 1.0573 0.04975 0.04165 0.0493 0.1154 1.0000 13.500 1.0514 0.05253 0.04447 0.0497 0.1106 1.0000 13.750 1.0459 0.05534 0.04728 0.0500 0.1064 1.0000 14.000 1.0410 0.05827 0.05032 0.0501 0.1017 1.0000 14.250 1.0346 0.06142 0.05349 0.0499 0.0979 1.0000 14.500 1.0301 0.06451 0.05663 0.0498 0.0941 1.0000 14.750 1.0248 0.06785 0.06007 0.0493 0.0903 1.0000 15.000 1.0196 0.07119 0.06341 0.0488 0.0871 1.0000 15.250 1.0153 0.07454 0.06682 0.0483 0.0839 1.0000 15.500 1.0100 0.07817 0.07056 0.0475 0.0808 1.0000 15.750 1.0056 0.08167 0.07410 0.0467 0.0780 1.0000 16.000 1.0040 0.08474 0.07714 0.0461 0.0756 1.0000 16.250 0.9963 0.08905 0.08162 0.0448 0.0728 1.0000 16.500 0.9915 0.09288 0.08554 0.0437 0.0705 1.0000 16.750 0.9887 0.09635 0.08902 0.0427 0.0682 1.0000 17.000 0.9851 0.10007 0.09280 0.0416 0.0662 1.0000 17.250 0.9743 0.10523 0.09813 0.0397 0.0642 1.0000 17.500 0.9667 0.10987 0.10287 0.0379 0.0623 1.0000 17.750 0.9643 0.11353 0.10656 0.0366 0.0605 1.0000 18.000 0.9661 0.11637 0.10938 0.0358 0.0589 1.0000 18.250 0.9447 0.12402 0.11726 0.0322 0.0575 1.0000 18.500 0.9184 0.13297 0.12641 0.0279 0.0563 1.0000 18.750 0.8650 0.14855 0.14225 0.0201 0.0549 1.0000