XFOIL Version 6.96 Calculated polar for: GOE 777 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.8525 0.08637 0.08270 -0.0646 1.0000 0.0335 -18.500 -0.8713 0.07966 0.07587 -0.0690 1.0000 0.0336 -18.250 -0.8843 0.07407 0.07017 -0.0726 1.0000 0.0338 -18.000 -0.8946 0.06898 0.06498 -0.0759 1.0000 0.0340 -17.750 -0.9034 0.06428 0.06018 -0.0789 1.0000 0.0342 -17.500 -0.9107 0.05997 0.05577 -0.0815 1.0000 0.0344 -17.250 -0.9166 0.05604 0.05173 -0.0837 1.0000 0.0347 -17.000 -0.9212 0.05243 0.04803 -0.0857 1.0000 0.0349 -16.750 -0.9245 0.04910 0.04459 -0.0873 1.0000 0.0352 -16.500 -0.9264 0.04604 0.04142 -0.0886 1.0000 0.0355 -16.250 -0.9233 0.04323 0.03847 -0.0906 0.9446 0.0359 -16.000 -0.9280 0.04123 0.03599 -0.0892 0.8234 0.0361 -15.750 -0.9268 0.03919 0.03357 -0.0892 0.7684 0.0364 -15.500 -0.9232 0.03724 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-0.0563 0.4889 0.6111 -1.000 0.3667 0.01144 0.00511 -0.0562 0.4867 0.6331 -0.750 0.3952 0.01147 0.00512 -0.0561 0.4845 0.6504 -0.500 0.4239 0.01161 0.00523 -0.0562 0.4819 0.6659 -0.250 0.4519 0.01163 0.00530 -0.0562 0.4800 0.6799 0.000 0.4801 0.01160 0.00531 -0.0561 0.4780 0.6933 0.250 0.5082 0.01156 0.00532 -0.0561 0.4757 0.7066 0.500 0.5367 0.01154 0.00532 -0.0561 0.4731 0.7173 0.750 0.5649 0.01150 0.00531 -0.0561 0.4705 0.7302 1.000 0.5932 0.01146 0.00528 -0.0561 0.4680 0.7427 1.250 0.6214 0.01146 0.00528 -0.0561 0.4653 0.7562 1.500 0.6493 0.01154 0.00537 -0.0561 0.4622 0.7707 1.750 0.6764 0.01146 0.00539 -0.0559 0.4595 0.7874 2.000 0.7034 0.01140 0.00541 -0.0556 0.4561 0.8073 2.250 0.7301 0.01134 0.00541 -0.0553 0.4526 0.8293 2.500 0.7568 0.01128 0.00541 -0.0550 0.4492 0.8517 2.750 0.7833 0.01130 0.00543 -0.0546 0.4456 0.8754 3.000 0.8101 0.01128 0.00553 -0.0543 0.4419 0.9021 3.250 0.8406 0.01129 0.00562 -0.0547 0.4371 0.9305 3.500 0.8782 0.01137 0.00569 -0.0567 0.4320 0.9509 3.750 0.9157 0.01150 0.00577 -0.0588 0.4267 0.9659 4.000 0.9539 0.01160 0.00590 -0.0611 0.4198 0.9773 4.250 0.9949 0.01175 0.00596 -0.0641 0.4127 0.9834 4.500 1.0348 0.01191 0.00611 -0.0669 0.4048 0.9902 4.750 1.0750 0.01211 0.00623 -0.0699 0.3964 0.9950 5.000 1.1158 0.01233 0.00642 -0.0730 0.3882 0.9993 5.250 1.1330 0.01255 0.00657 -0.0714 0.3814 1.0000 5.500 1.1472 0.01277 0.00675 -0.0692 0.3757 1.0000 5.750 1.1622 0.01300 0.00695 -0.0671 0.3702 1.0000 6.000 1.1758 0.01330 0.00718 -0.0648 0.3653 1.0000 6.250 1.1909 0.01358 0.00744 -0.0628 0.3613 1.0000 6.500 1.2075 0.01384 0.00770 -0.0610 0.3576 1.0000 6.750 1.2233 0.01415 0.00799 -0.0592 0.3541 1.0000 7.000 1.2365 0.01451 0.00831 -0.0570 0.3508 1.0000 7.250 1.2487 0.01494 0.00869 -0.0546 0.3476 1.0000 7.500 1.2659 0.01526 0.00904 -0.0532 0.3453 1.0000 7.750 1.2836 0.01562 0.00943 -0.0520 0.3430 1.0000 8.000 1.3009 0.01602 0.00985 -0.0508 0.3406 1.0000 8.250 1.3180 0.01649 0.01031 -0.0497 0.3383 1.0000 8.500 1.3346 0.01700 0.01082 -0.0486 0.3360 1.0000 8.750 1.3512 0.01758 0.01137 -0.0476 0.3337 1.0000 9.000 1.3697 0.01814 0.01190 -0.0469 0.3311 1.0000 9.250 1.3868 0.01869 0.01251 -0.0461 0.3296 1.0000 9.500 1.4040 0.01927 0.01314 -0.0454 0.3279 1.0000 9.750 1.4212 0.01989 0.01380 -0.0448 0.3263 1.0000 10.000 1.4381 0.02054 0.01449 -0.0442 0.3246 1.0000 10.250 1.4549 0.02123 0.01520 -0.0436 0.3229 1.0000 10.500 1.4714 0.02195 0.01595 -0.0431 0.3213 1.0000 10.750 1.4885 0.02266 0.01666 -0.0427 0.3197 1.0000 11.000 1.5065 0.02333 0.01732 -0.0422 0.3177 1.0000 11.250 1.5269 0.02391 0.01787 -0.0420 0.3152 1.0000 11.500 1.5375 0.02500 0.01906 -0.0413 0.3137 1.0000 11.750 1.5495 0.02606 0.02020 -0.0408 0.3120 1.0000 12.000 1.5626 0.02709 0.02129 -0.0404 0.3103 1.0000 12.250 1.5752 0.02816 0.02241 -0.0400 0.3084 1.0000 12.500 1.5868 0.02931 0.02359 -0.0396 0.3061 1.0000 12.750 1.5983 0.03047 0.02476 -0.0392 0.3036 1.0000 13.000 1.6166 0.03110 0.02536 -0.0389 0.3010 1.0000 13.250 1.6320 0.03199 0.02627 -0.0386 0.2992 1.0000 13.500 1.6380 0.03363 0.02802 -0.0381 0.2979 1.0000 13.750 1.6449 0.03522 0.02971 -0.0378 0.2963 1.0000 14.000 1.6515 0.03686 0.03143 -0.0375 0.2943 1.0000 14.250 1.6583 0.03851 0.03314 -0.0372 0.2921 1.0000 14.500 1.6674 0.03997 0.03464 -0.0370 0.2900 1.0000 14.750 1.6775 0.04135 0.03604 -0.0369 0.2880 1.0000 15.000 1.6942 0.04209 0.03677 -0.0367 0.2860 1.0000 15.250 1.7098 0.04293 0.03763 -0.0365 0.2839 1.0000 15.500 1.7056 0.04572 0.04056 -0.0363 0.2822 1.0000 15.750 1.7045 0.04829 0.04325 -0.0363 0.2801 1.0000 16.000 1.7054 0.05072 0.04576 -0.0363 0.2777 1.0000 16.250 1.7087 0.05291 0.04801 -0.0364 0.2750 1.0000 16.500 1.7156 0.05471 0.04981 -0.0365 0.2722 1.0000 16.750 1.7327 0.05532 0.05038 -0.0364 0.2692 1.0000 17.000 1.7176 0.05962 0.05486 -0.0366 0.2667 1.0000 17.250 1.7098 0.06317 0.05853 -0.0369 0.2637 1.0000 17.500 1.7090 0.06596 0.06138 -0.0372 0.2605 1.0000 17.750 1.7125 0.06822 0.06365 -0.0375 0.2573 1.0000 18.000 1.7190 0.07009 0.06553 -0.0376 0.2541 1.0000 18.250 1.7021 0.07483 0.07043 -0.0380 0.2509 1.0000 18.500 1.6959 0.07834 0.07404 -0.0385 0.2473 1.0000 18.750 1.6944 0.08128 0.07701 -0.0389 0.2439 1.0000 19.000 1.6995 0.08335 0.07907 -0.0392 0.2403 1.0000 19.250 1.6759 0.08907 0.08497 -0.0398 0.2357 1.0000