XFOIL Version 6.96 Calculated polar for: GOE 604 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -0.8181 0.08397 0.08102 -0.0709 1.0000 0.0171 -17.750 -0.8637 0.07426 0.07117 -0.0769 1.0000 0.0169 -17.500 -0.9248 0.06279 0.05951 -0.0841 1.0000 0.0167 -17.250 -0.9865 0.05126 0.04778 -0.0916 1.0000 0.0166 -17.000 -1.0310 0.04127 0.03756 -0.0990 1.0000 0.0165 -16.750 -1.0528 0.03465 0.03076 -0.1043 1.0000 0.0166 -16.500 -1.0647 0.03078 0.02676 -0.1064 1.0000 0.0168 -16.250 -1.0718 0.02841 0.02431 -0.1061 1.0000 0.0170 -15.750 -1.0530 0.02509 0.02081 -0.1070 0.9859 0.0176 -15.500 -1.0318 0.02394 0.01958 -0.1081 0.9781 0.0180 -15.250 -1.0065 0.02277 0.01835 -0.1099 0.9708 0.0184 -15.000 -0.9747 0.02175 0.01728 -0.1123 0.9645 0.0189 -14.750 -0.9394 0.02083 0.01631 -0.1151 0.9570 0.0194 -14.500 -0.9045 0.02001 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0.5645 0.00948 0.00252 -0.0701 0.3586 0.3069 1.000 0.5899 0.00952 0.00258 -0.0695 0.3514 0.3242 1.250 0.6146 0.00959 0.00265 -0.0689 0.3447 0.3420 1.500 0.6402 0.00960 0.00270 -0.0684 0.3408 0.3620 2.000 0.6895 0.00962 0.00285 -0.0671 0.3324 0.4222 2.250 0.7131 0.00963 0.00294 -0.0663 0.3283 0.4615 2.500 0.7371 0.00958 0.00301 -0.0655 0.3257 0.5102 2.750 0.7600 0.00952 0.00310 -0.0646 0.3226 0.5692 3.000 0.7812 0.00943 0.00321 -0.0633 0.3191 0.6439 3.250 0.8001 0.00934 0.00333 -0.0615 0.3152 0.7240 3.500 0.8165 0.00921 0.00346 -0.0590 0.3123 0.8169 3.750 0.8502 0.00912 0.00367 -0.0602 0.3100 0.9240 4.000 0.9273 0.00939 0.00393 -0.0709 0.3056 0.9626 4.250 0.9708 0.00959 0.00410 -0.0743 0.3022 0.9739 4.500 1.0037 0.00978 0.00426 -0.0755 0.2993 0.9825 4.750 1.0374 0.00998 0.00443 -0.0770 0.2962 0.9902 5.000 1.0763 0.01016 0.00460 -0.0795 0.2943 0.9978 5.250 1.1144 0.01033 0.00476 -0.0818 0.2920 1.0000 5.500 1.1338 0.01045 0.00488 -0.0802 0.2898 1.0000 5.750 1.1529 0.01060 0.00502 -0.0786 0.2872 1.0000 6.000 1.1710 0.01078 0.00517 -0.0768 0.2840 1.0000 6.250 1.1888 0.01097 0.00535 -0.0750 0.2810 1.0000 6.500 1.2069 0.01112 0.00550 -0.0732 0.2790 1.0000 6.750 1.2238 0.01125 0.00565 -0.0711 0.2770 1.0000 7.000 1.2404 0.01140 0.00580 -0.0690 0.2743 1.0000 7.250 1.2570 0.01158 0.00597 -0.0670 0.2714 1.0000 7.500 1.2740 0.01179 0.00618 -0.0652 0.2687 1.0000 7.750 1.2908 0.01202 0.00640 -0.0633 0.2659 1.0000 8.000 1.3092 0.01224 0.00663 -0.0618 0.2636 1.0000 8.250 1.3285 0.01244 0.00685 -0.0605 0.2612 1.0000 8.500 1.3474 0.01268 0.00709 -0.0592 0.2582 1.0000 8.750 1.3648 0.01298 0.00739 -0.0576 0.2540 1.0000 9.000 1.3813 0.01334 0.00773 -0.0561 0.2491 1.0000 9.250 1.3994 0.01365 0.00805 -0.0548 0.2442 1.0000 9.500 1.4158 0.01405 0.00844 -0.0533 0.2387 1.0000 9.750 1.4316 0.01450 0.00888 -0.0518 0.2329 1.0000 10.000 1.4455 0.01505 0.00940 -0.0502 0.2243 1.0000 10.250 1.4575 0.01572 0.01003 -0.0483 0.2133 1.0000 10.500 1.4617 0.01681 0.01103 -0.0457 0.1960 1.0000 10.750 1.4655 0.01801 0.01216 -0.0433 0.1821 1.0000 11.000 1.4709 0.01920 0.01332 -0.0413 0.1725 1.0000 11.250 1.4788 0.02034 0.01445 -0.0397 0.1664 1.0000 11.500 1.4862 0.02157 0.01568 -0.0382 0.1613 1.0000 11.750 1.4927 0.02293 0.01705 -0.0369 0.1566 1.0000 12.000 1.5036 0.02406 0.01822 -0.0360 0.1543 1.0000 12.250 1.5135 0.02531 0.01950 -0.0352 0.1522 1.0000 12.500 1.5231 0.02663 0.02086 -0.0344 0.1507 1.0000 12.750 1.5291 0.02829 0.02255 -0.0336 0.1482 1.0000 13.000 1.5341 0.03010 0.02440 -0.0329 0.1458 1.0000 13.250 1.5388 0.03200 0.02635 -0.0323 0.1437 1.0000 13.500 1.5453 0.03378 0.02818 -0.0318 0.1421 1.0000 13.750 1.5528 0.03549 0.02996 -0.0315 0.1410 1.0000 14.000 1.5589 0.03737 0.03190 -0.0312 0.1398 1.0000 14.250 1.5634 0.03943 0.03400 -0.0308 0.1384 1.0000 14.500 1.5640 0.04187 0.03649 -0.0305 0.1358 1.0000 14.750 1.5634 0.04447 0.03914 -0.0302 0.1339 1.0000 15.000 1.5612 0.04728 0.04200 -0.0299 0.1320 1.0000 15.250 1.5591 0.05010 0.04489 -0.0297 0.1305 1.0000 15.500 1.5594 0.05272 0.04756 -0.0296 0.1293 1.0000 15.750 1.5625 0.05505 0.04996 -0.0296 0.1280 1.0000 16.000 1.5618 0.05784 0.05282 -0.0296 0.1262 1.0000 16.250 1.5610 0.06065 0.05569 -0.0296 0.1247 1.0000 16.500 1.5567 0.06386 0.05894 -0.0297 0.1220 1.0000 16.750 1.5510 0.06732 0.06245 -0.0299 0.1202 1.0000 17.000 1.5432 0.07104 0.06622 -0.0301 0.1175 1.0000 17.250 1.5428 0.07390 0.06914 -0.0304 0.1156 1.0000 17.500 1.5371 0.07745 0.07275 -0.0307 0.1126 1.0000 17.750 1.5275 0.08151 0.07685 -0.0312 0.1090 1.0000 18.000 1.5184 0.08553 0.08089 -0.0317 0.1047 1.0000 18.250 1.4978 0.09103 0.08639 -0.0325 0.0958 1.0000 18.500 1.4741 0.09707 0.09243 -0.0335 0.0858 1.0000 18.750 1.4372 0.10492 0.10023 -0.0350 0.0703 1.0000 19.000 1.4148 0.11101 0.10632 -0.0364 0.0616 1.0000