XFOIL Version 6.96 Calculated polar for: GOE 434 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9089 0.09013 0.08641 -0.0801 1.0000 0.0563 -19.000 -0.9051 0.08734 0.08360 -0.0817 1.0000 0.0567 -18.750 -0.9011 0.08458 0.08081 -0.0832 1.0000 0.0572 -18.500 -0.8992 0.08151 0.07771 -0.0849 1.0000 0.0577 -18.250 -0.8950 0.07882 0.07499 -0.0864 1.0000 0.0582 -18.000 -0.8904 0.07618 0.07231 -0.0878 1.0000 0.0587 -17.750 -0.8882 0.07322 0.06930 -0.0895 1.0000 0.0591 -17.500 -0.8835 0.07058 0.06662 -0.0909 1.0000 0.0595 -17.250 -0.8785 0.06799 0.06398 -0.0924 1.0000 0.0599 -17.000 -0.8738 0.06572 0.06173 -0.0934 1.0000 0.0606 -16.750 -0.8710 0.06307 0.05907 -0.0948 1.0000 0.0612 -16.500 -0.8651 0.06070 0.05670 -0.0962 0.9987 0.0617 -16.000 -0.8431 0.05531 0.05124 -0.1016 0.9821 0.0628 -15.750 -0.8330 0.05303 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0.5580 0.2962 -1.500 0.4976 0.00911 0.00327 -0.1447 0.5552 0.3008 -1.250 0.5276 0.00910 0.00326 -0.1449 0.5521 0.3062 -1.000 0.5574 0.00915 0.00329 -0.1450 0.5484 0.3102 -0.750 0.5875 0.00921 0.00333 -0.1452 0.5449 0.3137 -0.500 0.6178 0.00920 0.00333 -0.1454 0.5427 0.3164 -0.250 0.6481 0.00920 0.00333 -0.1456 0.5394 0.3184 0.000 0.6782 0.00915 0.00331 -0.1458 0.5357 0.3234 0.250 0.7079 0.00915 0.00332 -0.1459 0.5318 0.3284 0.500 0.7372 0.00920 0.00336 -0.1460 0.5278 0.3327 0.750 0.7667 0.00925 0.00340 -0.1461 0.5239 0.3364 1.000 0.7969 0.00926 0.00342 -0.1463 0.5203 0.3390 1.250 0.8266 0.00929 0.00345 -0.1464 0.5157 0.3410 1.500 0.8557 0.00930 0.00346 -0.1465 0.5104 0.3463 1.750 0.8842 0.00935 0.00350 -0.1464 0.5045 0.3517 2.000 0.9139 0.00936 0.00355 -0.1466 0.4991 0.3564 2.250 0.9426 0.00943 0.00360 -0.1466 0.4923 0.3604 2.500 0.9705 0.00953 0.00367 -0.1464 0.4846 0.3634 2.750 0.9990 0.00962 0.00373 -0.1463 0.4763 0.3656 3.000 1.0261 0.00972 0.00381 -0.1461 0.4678 0.3728 3.250 1.0543 0.00980 0.00391 -0.1461 0.4596 0.3786 3.500 1.0804 0.00997 0.00404 -0.1456 0.4497 0.3836 3.750 1.1075 0.01012 0.00416 -0.1454 0.4396 0.3884 4.000 1.1329 0.01033 0.00432 -0.1449 0.4287 0.3938 4.250 1.1584 0.01051 0.00450 -0.1444 0.4177 0.4031 4.500 1.1839 0.01070 0.00468 -0.1439 0.4080 0.4102 4.750 1.2077 0.01096 0.00489 -0.1432 0.3970 0.4157 5.000 1.2327 0.01116 0.00508 -0.1426 0.3869 0.4247 5.250 1.2549 0.01146 0.00535 -0.1416 0.3749 0.4340 5.500 1.2761 0.01176 0.00561 -0.1405 0.3614 0.4419 5.750 1.2942 0.01209 0.00590 -0.1387 0.3461 0.4531 6.000 1.3095 0.01259 0.00633 -0.1367 0.3260 0.4644 6.250 1.3219 0.01332 0.00693 -0.1343 0.2989 0.4747 6.500 1.3287 0.01430 0.00775 -0.1313 0.2679 0.4873 6.750 1.3372 0.01523 0.00857 -0.1286 0.2460 0.4979 7.000 1.3494 0.01601 0.00932 -0.1265 0.2326 0.5125 7.250 1.3625 0.01679 0.01007 -0.1246 0.2229 0.5248 7.500 1.3787 0.01743 0.01074 -0.1232 0.2171 0.5395 7.750 1.3928 0.01821 0.01152 -0.1217 0.2116 0.5515 8.000 1.4081 0.01896 0.01231 -0.1203 0.2070 0.5654 8.250 1.4250 0.01966 0.01303 -0.1192 0.2039 0.5771 8.500 1.4401 0.02047 0.01389 -0.1180 0.2006 0.5909 9.000 1.4657 0.02254 0.01601 -0.1154 0.1938 0.6168 9.250 1.4806 0.02348 0.01701 -0.1144 0.1919 0.6299 9.500 1.4972 0.02434 0.01794 -0.1136 0.1903 0.6454 9.750 1.5119 0.02535 0.01902 -0.1127 0.1885 0.6615 10.000 1.5255 0.02646 0.02020 -0.1118 0.1865 0.6799 10.250 1.5374 0.02772 0.02153 -0.1108 0.1844 0.7015 10.500 1.5473 0.02916 0.02304 -0.1097 0.1822 0.7259 10.750 1.5559 0.03071 0.02466 -0.1086 0.1797 0.7521 11.000 1.5645 0.03232 0.02637 -0.1076 0.1777 0.7805 11.250 1.5793 0.03338 0.02755 -0.1069 0.1766 0.8152 11.500 1.5878 0.03443 0.02892 -0.1054 0.1754 1.0000 11.750 1.5997 0.03583 0.03034 -0.1047 0.1738 1.0000 12.000 1.6092 0.03747 0.03201 -0.1039 0.1720 1.0000 12.250 1.6182 0.03916 0.03371 -0.1031 0.1702 1.0000 12.500 1.6249 0.04108 0.03564 -0.1022 0.1683 1.0000 12.750 1.6303 0.04311 0.03768 -0.1013 0.1661 1.0000 13.000 1.6352 0.04522 0.03981 -0.1005 0.1642 1.0000 13.250 1.6468 0.04673 0.04137 -0.0999 0.1632 1.0000 13.500 1.6583 0.04821 0.04289 -0.0994 0.1619 1.0000 13.750 1.6677 0.04993 0.04464 -0.0987 0.1602 1.0000 14.000 1.6747 0.05189 0.04661 -0.0981 0.1583 1.0000 14.250 1.6818 0.05381 0.04854 -0.0974 0.1561 1.0000 14.500 1.6860 0.05606 0.05081 -0.0968 0.1540 1.0000 14.750 1.6885 0.05849 0.05326 -0.0961 0.1518 1.0000 15.000 1.7002 0.06000 0.05481 -0.0956 0.1506 1.0000 15.250 1.7095 0.06172 0.05657 -0.0951 0.1488 1.0000 15.500 1.7151 0.06389 0.05877 -0.0947 0.1467 1.0000 15.750 1.7209 0.06601 0.06090 -0.0942 0.1443 1.0000 16.000 1.7243 0.06838 0.06327 -0.0936 0.1416 1.0000 16.250 1.7285 0.07074 0.06567 -0.0932 0.1394 1.0000 16.500 1.7360 0.07269 0.06766 -0.0928 0.1367 1.0000 16.750 1.7407 0.07495 0.06991 -0.0924 0.1331 1.0000 17.000 1.7388 0.07798 0.07296 -0.0920 0.1295 1.0000 17.250 1.7442 0.08020 0.07520 -0.0917 0.1253 1.0000 17.500 1.7418 0.08331 0.07829 -0.0914 0.1201 1.0000 17.750 1.7407 0.08628 0.08127 -0.0912 0.1141 1.0000 18.000 1.7371 0.08954 0.08450 -0.0910 0.1070 1.0000 18.250 1.7283 0.09347 0.08842 -0.0909 0.1004 1.0000 18.500 1.7220 0.09713 0.09206 -0.0909 0.0945 1.0000