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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0143 0.08039 0.07688 -0.0642 1.0000 0.0261 -19.500 -1.0290 0.07477 0.07118 -0.0675 1.0000 0.0263 -19.250 -1.0417 0.06945 0.06577 -0.0706 1.0000 0.0265 -19.000 -1.0528 0.06441 0.06064 -0.0735 1.0000 0.0266 -18.750 -1.0610 0.05979 0.05594 -0.0762 1.0000 0.0268 -18.500 -1.0673 0.05556 0.05163 -0.0786 1.0000 0.0269 -18.250 -1.0715 0.05174 0.04774 -0.0806 1.0000 0.0271 -18.000 -1.0735 0.04834 0.04426 -0.0823 1.0000 0.0273 -17.750 -1.0740 0.04522 0.04107 -0.0838 1.0000 0.0276 -17.500 -1.0726 0.04242 0.03820 -0.0849 1.0000 0.0278 -17.250 -1.0730 0.04021 0.03565 -0.0849 0.8664 0.0280 -17.000 -1.0701 0.03818 0.03325 -0.0850 0.7859 0.0283 -16.750 -1.0640 0.03620 0.03103 -0.0855 0.7456 0.0285 -16.500 -1.0562 0.03436 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-0.0584 0.4728 0.2199 -2.000 0.2688 0.00964 0.00317 -0.0581 0.4712 0.2988 -1.750 0.2963 0.00944 0.00311 -0.0580 0.4696 0.3439 -1.500 0.3239 0.00928 0.00307 -0.0580 0.4678 0.3850 -1.250 0.3509 0.00910 0.00304 -0.0578 0.4656 0.4334 -1.000 0.3764 0.00889 0.00308 -0.0574 0.4630 0.5170 -0.750 0.4042 0.00876 0.00311 -0.0574 0.4617 0.5703 -0.500 0.4333 0.00871 0.00312 -0.0575 0.4604 0.5962 -0.250 0.4625 0.00866 0.00314 -0.0576 0.4587 0.6137 0.000 0.4918 0.00864 0.00314 -0.0578 0.4566 0.6274 0.250 0.5212 0.00862 0.00314 -0.0581 0.4543 0.6400 0.500 0.5504 0.00861 0.00314 -0.0582 0.4517 0.6508 0.750 0.5793 0.00863 0.00315 -0.0584 0.4489 0.6622 1.000 0.6078 0.00869 0.00320 -0.0585 0.4454 0.6728 1.250 0.6371 0.00868 0.00323 -0.0588 0.4433 0.6828 1.500 0.6668 0.00868 0.00325 -0.0591 0.4408 0.6915 1.750 0.6958 0.00865 0.00327 -0.0593 0.4376 0.7026 2.250 0.7525 0.00869 0.00333 -0.0595 0.4296 0.7289 2.500 0.7810 0.00870 0.00338 -0.0597 0.4257 0.7439 2.750 0.8093 0.00868 0.00343 -0.0598 0.4208 0.7639 3.000 0.8366 0.00870 0.00349 -0.0597 0.4146 0.7866 3.250 0.8636 0.00873 0.00358 -0.0596 0.4081 0.8099 3.500 0.8899 0.00878 0.00367 -0.0594 0.3993 0.8372 3.750 0.9153 0.00886 0.00380 -0.0590 0.3899 0.8678 4.000 0.9389 0.00901 0.00397 -0.0582 0.3789 0.9017 4.250 0.9659 0.00918 0.00418 -0.0581 0.3688 0.9370 4.500 0.9989 0.00947 0.00443 -0.0594 0.3593 0.9614 4.750 1.0334 0.00978 0.00469 -0.0612 0.3511 0.9753 5.000 1.0685 0.01006 0.00493 -0.0631 0.3448 0.9841 5.250 1.1038 0.01032 0.00515 -0.0650 0.3400 0.9907 5.500 1.1406 0.01063 0.00541 -0.0673 0.3351 0.9943 5.750 1.1775 0.01093 0.00568 -0.0697 0.3307 0.9977 6.000 1.2134 0.01113 0.00588 -0.0718 0.3282 1.0000 6.250 1.2303 0.01131 0.00605 -0.0700 0.3258 1.0000 6.500 1.2468 0.01152 0.00625 -0.0681 0.3234 1.0000 6.750 1.2627 0.01176 0.00648 -0.0662 0.3210 1.0000 7.000 1.2770 0.01204 0.00675 -0.0640 0.3183 1.0000 7.250 1.2898 0.01238 0.00707 -0.0615 0.3155 1.0000 7.500 1.3074 0.01257 0.00728 -0.0599 0.3145 1.0000 7.750 1.3253 0.01278 0.00752 -0.0585 0.3132 1.0000 8.000 1.3439 0.01304 0.00779 -0.0573 0.3119 1.0000 8.250 1.3628 0.01333 0.00810 -0.0562 0.3103 1.0000 8.500 1.3812 0.01368 0.00847 -0.0551 0.3086 1.0000 8.750 1.3989 0.01409 0.00888 -0.0541 0.3069 1.0000 9.000 1.4156 0.01457 0.00938 -0.0530 0.3051 1.0000 9.250 1.4312 0.01515 0.00996 -0.0519 0.3033 1.0000 9.500 1.4450 0.01585 0.01066 -0.0506 0.3009 1.0000 9.750 1.4620 0.01645 0.01129 -0.0499 0.2994 1.0000 10.000 1.4818 0.01693 0.01181 -0.0496 0.2983 1.0000 10.250 1.5006 0.01749 0.01242 -0.0492 0.2971 1.0000 10.500 1.5187 0.01812 0.01309 -0.0489 0.2957 1.0000 10.750 1.5358 0.01884 0.01384 -0.0485 0.2944 1.0000 11.000 1.5520 0.01964 0.01468 -0.0481 0.2928 1.0000 11.250 1.5667 0.02058 0.01564 -0.0477 0.2911 1.0000 11.500 1.5792 0.02171 0.01680 -0.0473 0.2892 1.0000 11.750 1.5889 0.02305 0.01814 -0.0466 0.2868 1.0000 12.000 1.5986 0.02437 0.01947 -0.0460 0.2842 1.0000 12.250 1.6140 0.02541 0.02058 -0.0460 0.2832 1.0000 12.500 1.6285 0.02651 0.02174 -0.0459 0.2818 1.0000 12.750 1.6414 0.02771 0.02300 -0.0458 0.2804 1.0000 13.000 1.6529 0.02904 0.02437 -0.0455 0.2788 1.0000 13.250 1.6636 0.03041 0.02578 -0.0453 0.2771 1.0000 13.500 1.6714 0.03204 0.02746 -0.0450 0.2754 1.0000 13.750 1.6772 0.03381 0.02925 -0.0445 0.2735 1.0000 14.000 1.6824 0.03557 0.03103 -0.0440 0.2715 1.0000 14.250 1.6898 0.03711 0.03258 -0.0435 0.2692 1.0000 14.500 1.6988 0.03877 0.03432 -0.0434 0.2681 1.0000 14.750 1.7064 0.04057 0.03619 -0.0434 0.2665 1.0000 15.000 1.7140 0.04233 0.03802 -0.0433 0.2645 1.0000 15.250 1.7194 0.04433 0.04007 -0.0432 0.2623 1.0000 15.500 1.7239 0.04639 0.04216 -0.0431 0.2600 1.0000 15.750 1.7231 0.04894 0.04472 -0.0428 0.2570 1.0000 16.000 1.7280 0.05088 0.04668 -0.0426 0.2543 1.0000 16.250 1.7329 0.05302 0.04891 -0.0426 0.2524 1.0000 16.500 1.7387 0.05503 0.05099 -0.0427 0.2500 1.0000 16.750 1.7432 0.05715 0.05315 -0.0427 0.2472 1.0000 17.000 1.7403 0.06001 0.05603 -0.0426 0.2440 1.0000 17.250 1.7401 0.06253 0.05856 -0.0424 0.2406 1.0000 17.500 1.7444 0.06475 0.06087 -0.0426 0.2381 1.0000 17.750 1.7466 0.06716 0.06333 -0.0427 0.2344 1.0000 18.000 1.7449 0.06996 0.06613 -0.0427 0.2301 1.0000 18.250 1.7388 0.07323 0.06945 -0.0427 0.2262 1.0000 18.500 1.7419 0.07554 0.07182 -0.0429 0.2217 1.0000 18.750 1.7315 0.07935 0.07564 -0.0430 0.2159 1.0000 19.000 1.7271 0.08253 0.07884 -0.0432 0.2099 1.0000 19.250 1.7103 0.08710 0.08342 -0.0433 0.2022 1.0000