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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7834 0.11374 0.11023 -0.0455 1.0000 0.0261 -19.500 -0.8173 0.10396 0.10027 -0.0515 1.0000 0.0263 -19.250 -0.8447 0.09559 0.09174 -0.0567 1.0000 0.0265 -19.000 -0.8698 0.08888 0.08459 -0.0600 0.8457 0.0266 -18.750 -0.8905 0.08250 0.07784 -0.0635 0.7892 0.0267 -18.500 -0.9069 0.07651 0.07158 -0.0670 0.7597 0.0269 -18.250 -0.9200 0.07108 0.06594 -0.0703 0.7379 0.0270 -18.000 -0.9320 0.06592 0.06061 -0.0734 0.7207 0.0272 -17.750 -0.9414 0.06114 0.05568 -0.0763 0.7054 0.0274 -17.500 -0.9490 0.05676 0.05114 -0.0789 0.6908 0.0276 -17.250 -0.9541 0.05284 0.04708 -0.0811 0.6775 0.0278 -16.750 -0.9574 0.04627 0.04023 -0.0845 0.6502 0.0282 -16.500 -0.9561 0.04348 0.03730 -0.0857 0.6375 0.0285 -16.250 -0.9531 0.04096 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3.500 0.8825 0.01153 0.00509 -0.0581 0.3759 0.8256 3.750 0.9058 0.01170 0.00529 -0.0574 0.3684 0.8522 4.000 0.9293 0.01188 0.00550 -0.0568 0.3610 0.8764 4.250 0.9529 0.01212 0.00576 -0.0562 0.3545 0.9026 4.500 0.9820 0.01237 0.00602 -0.0567 0.3485 0.9296 4.750 1.0168 0.01272 0.00635 -0.0586 0.3425 0.9543 5.000 1.0507 0.01306 0.00665 -0.0604 0.3378 0.9754 5.250 1.0841 0.01335 0.00693 -0.0620 0.3341 0.9895 5.500 1.1176 0.01368 0.00724 -0.0638 0.3304 0.9985 5.750 1.1351 0.01398 0.00751 -0.0623 0.3274 1.0000 6.000 1.1470 0.01430 0.00781 -0.0598 0.3247 1.0000 6.250 1.1598 0.01461 0.00810 -0.0574 0.3224 1.0000 6.500 1.1763 0.01489 0.00840 -0.0558 0.3206 1.0000 6.750 1.1933 0.01523 0.00875 -0.0544 0.3186 1.0000 7.000 1.2103 0.01561 0.00914 -0.0531 0.3166 1.0000 7.250 1.2271 0.01606 0.00959 -0.0520 0.3146 1.0000 7.500 1.2435 0.01656 0.01010 -0.0508 0.3126 1.0000 7.750 1.2593 0.01713 0.01068 -0.0497 0.3108 1.0000 8.000 1.2744 0.01779 0.01133 -0.0487 0.3089 1.0000 8.250 1.2889 0.01853 0.01207 -0.0477 0.3070 1.0000 8.500 1.3064 0.01915 0.01273 -0.0472 0.3057 1.0000 8.750 1.3242 0.01980 0.01342 -0.0467 0.3043 1.0000 9.000 1.3411 0.02052 0.01418 -0.0462 0.3028 1.0000 9.250 1.3572 0.02133 0.01502 -0.0458 0.3013 1.0000 9.500 1.3728 0.02220 0.01593 -0.0454 0.2999 1.0000 9.750 1.3875 0.02315 0.01692 -0.0450 0.2985 1.0000 10.000 1.4014 0.02419 0.01799 -0.0446 0.2970 1.0000 10.250 1.4146 0.02530 0.01912 -0.0442 0.2956 1.0000 10.500 1.4272 0.02648 0.02032 -0.0438 0.2943 1.0000 10.750 1.4387 0.02773 0.02160 -0.0434 0.2928 1.0000 11.000 1.4498 0.02899 0.02287 -0.0429 0.2912 1.0000 11.250 1.4622 0.03019 0.02411 -0.0425 0.2898 1.0000 11.500 1.4745 0.03146 0.02545 -0.0424 0.2884 1.0000 11.750 1.4860 0.03280 0.02686 -0.0421 0.2868 1.0000 12.000 1.4966 0.03420 0.02831 -0.0419 0.2852 1.0000 12.250 1.5071 0.03559 0.02976 -0.0416 0.2837 1.0000 12.500 1.5160 0.03715 0.03136 -0.0414 0.2819 1.0000 12.750 1.5240 0.03880 0.03305 -0.0411 0.2798 1.0000 13.000 1.5298 0.04065 0.03491 -0.0408 0.2774 1.0000 13.250 1.5370 0.04232 0.03657 -0.0404 0.2750 1.0000 13.500 1.5452 0.04404 0.03836 -0.0403 0.2733 1.0000 13.750 1.5536 0.04577 0.04018 -0.0403 0.2718 1.0000 14.000 1.5618 0.04752 0.04200 -0.0402 0.2701 1.0000 14.250 1.5683 0.04945 0.04400 -0.0402 0.2681 1.0000 14.500 1.5755 0.05130 0.04589 -0.0402 0.2661 1.0000 14.750 1.5813 0.05329 0.04793 -0.0401 0.2640 1.0000 15.000 1.5871 0.05528 0.04993 -0.0401 0.2618 1.0000 15.250 1.5951 0.05697 0.05163 -0.0400 0.2598 1.0000 15.500 1.6013 0.05897 0.05371 -0.0401 0.2581 1.0000 15.750 1.6060 0.06116 0.05600 -0.0402 0.2564 1.0000 16.000 1.6117 0.06325 0.05816 -0.0403 0.2543 1.0000 16.250 1.6155 0.06553 0.06051 -0.0404 0.2518 1.0000 16.500 1.6171 0.06807 0.06308 -0.0405 0.2488 1.0000 16.750 1.6200 0.07038 0.06538 -0.0406 0.2457 1.0000 17.000 1.6205 0.07309 0.06820 -0.0408 0.2428 1.0000 17.250 1.6199 0.07595 0.07114 -0.0410 0.2395 1.0000 17.500 1.6200 0.07872 0.07396 -0.0413 0.2358 1.0000 17.750 1.6169 0.08183 0.07708 -0.0416 0.2319 1.0000 18.000 1.6154 0.08482 0.08017 -0.0419 0.2281 1.0000 18.250 1.6100 0.08828 0.08370 -0.0422 0.2236 1.0000 18.500 1.6048 0.09172 0.08714 -0.0426 0.2190 1.0000 18.750 1.5989 0.09531 0.09083 -0.0431 0.2140 1.0000 19.000 1.5896 0.09931 0.09486 -0.0436 0.2081 1.0000 19.250 1.5793 0.10345 0.09904 -0.0442 0.2024 1.0000