XFOIL Version 6.96 Calculated polar for: GOE 619 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.6664 0.12698 0.12477 -0.0452 1.0000 0.0198 -17.500 -0.6934 0.11808 0.11578 -0.0499 1.0000 0.0203 -17.250 -0.7160 0.11030 0.10792 -0.0540 1.0000 0.0205 -17.000 -0.7354 0.10334 0.10088 -0.0576 1.0000 0.0208 -16.750 -0.7565 0.09630 0.09376 -0.0614 1.0000 0.0209 -16.500 -0.7768 0.08959 0.08697 -0.0650 1.0000 0.0211 -16.250 -0.7958 0.08329 0.08059 -0.0683 1.0000 0.0212 -16.000 -0.8152 0.07718 0.07441 -0.0716 1.0000 0.0213 -15.750 -0.8375 0.07097 0.06812 -0.0750 1.0000 0.0214 -15.500 -0.8650 0.06455 0.06162 -0.0784 1.0000 0.0214 -15.250 -0.8981 0.05779 0.05477 -0.0820 1.0000 0.0214 -15.000 -0.9428 0.05012 0.04701 -0.0857 1.0000 0.0214 -14.750 -1.0061 0.03912 0.03585 -0.0935 0.9991 0.0212 -14.500 -1.0066 0.02917 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0.5475 0.00835 0.00174 -0.1032 0.4556 0.2416 0.750 0.5720 0.00848 0.00181 -0.1025 0.4352 0.2520 1.000 0.5960 0.00864 0.00190 -0.1016 0.4133 0.2617 1.250 0.6199 0.00881 0.00200 -0.1007 0.3916 0.2706 1.500 0.6438 0.00900 0.00210 -0.0999 0.3697 0.2786 1.750 0.6664 0.00922 0.00223 -0.0988 0.3447 0.2895 2.000 0.6899 0.00940 0.00235 -0.0979 0.3247 0.3013 2.250 0.7137 0.00956 0.00247 -0.0970 0.3088 0.3150 2.500 0.7377 0.00969 0.00258 -0.0961 0.2968 0.3280 2.750 0.7621 0.00980 0.00269 -0.0954 0.2863 0.3437 3.250 0.8085 0.01007 0.00297 -0.0935 0.2628 0.3923 3.500 0.8322 0.01019 0.00311 -0.0926 0.2534 0.4125 3.750 0.8552 0.01034 0.00326 -0.0916 0.2437 0.4338 4.000 0.8785 0.01045 0.00340 -0.0907 0.2364 0.4593 4.250 0.9011 0.01058 0.00355 -0.0896 0.2291 0.4845 4.500 0.9242 0.01065 0.00369 -0.0887 0.2245 0.5166 4.750 0.9409 0.01036 0.00390 -0.0865 0.2199 0.7207 5.250 1.0249 0.01036 0.00442 -0.0928 0.2097 1.0000 5.500 1.0466 0.01055 0.00458 -0.0915 0.2050 1.0000 5.750 1.0675 0.01077 0.00476 -0.0901 0.1998 1.0000 6.000 1.0888 0.01094 0.00492 -0.0888 0.1965 1.0000 6.250 1.1086 0.01113 0.00510 -0.0872 0.1919 1.0000 6.500 1.1261 0.01139 0.00531 -0.0852 0.1845 1.0000 6.750 1.1447 0.01163 0.00551 -0.0834 0.1762 1.0000 7.000 1.1615 0.01196 0.00577 -0.0813 0.1657 1.0000 7.250 1.1768 0.01236 0.00608 -0.0791 0.1505 1.0000 7.500 1.1863 0.01302 0.00656 -0.0759 0.1242 1.0000 7.750 1.1795 0.01447 0.00767 -0.0703 0.0672 1.0000 8.000 1.1934 0.01502 0.00817 -0.0681 0.0579 1.0000 8.250 1.2097 0.01547 0.00861 -0.0663 0.0542 1.0000 8.500 1.2269 0.01589 0.00902 -0.0647 0.0514 1.0000 8.750 1.2450 0.01627 0.00941 -0.0632 0.0504 1.0000 9.000 1.2622 0.01670 0.00985 -0.0617 0.0489 1.0000 9.250 1.2790 0.01718 0.01034 -0.0602 0.0473 1.0000 9.500 1.2947 0.01772 0.01087 -0.0586 0.0453 1.0000 9.750 1.3106 0.01827 0.01143 -0.0571 0.0432 1.0000 10.000 1.3275 0.01878 0.01196 -0.0558 0.0422 1.0000 10.250 1.3432 0.01938 0.01255 -0.0544 0.0397 1.0000 10.500 1.3570 0.02010 0.01326 -0.0528 0.0363 1.0000 11.000 1.3708 0.02256 0.01563 -0.0485 0.0130 1.0000 11.250 1.3839 0.02344 0.01654 -0.0471 0.0120 1.0000 11.500 1.3968 0.02436 0.01750 -0.0458 0.0112 1.0000 11.750 1.4092 0.02533 0.01851 -0.0446 0.0108 1.0000 12.000 1.4199 0.02646 0.01969 -0.0433 0.0101 1.0000 12.250 1.4318 0.02754 0.02081 -0.0422 0.0098 1.0000 12.500 1.4431 0.02867 0.02199 -0.0411 0.0095 1.0000 12.750 1.4536 0.02990 0.02327 -0.0400 0.0091 1.0000 13.000 1.4635 0.03121 0.02463 -0.0390 0.0088 1.0000 13.250 1.4722 0.03266 0.02613 -0.0380 0.0085 1.0000 13.500 1.4797 0.03424 0.02776 -0.0370 0.0082 1.0000 13.750 1.4850 0.03606 0.02964 -0.0360 0.0079 1.0000 14.000 1.4921 0.03776 0.03140 -0.0352 0.0078 1.0000 14.250 1.4988 0.03955 0.03325 -0.0346 0.0076 1.0000 14.500 1.5041 0.04151 0.03527 -0.0339 0.0075 1.0000 14.750 1.5090 0.04355 0.03737 -0.0333 0.0073 1.0000 15.000 1.5126 0.04577 0.03966 -0.0328 0.0071 1.0000 15.250 1.5153 0.04815 0.04210 -0.0324 0.0070 1.0000 15.500 1.5172 0.05065 0.04468 -0.0320 0.0069 1.0000 15.750 1.5181 0.05331 0.04740 -0.0318 0.0067 1.0000 16.000 1.5172 0.05623 0.05040 -0.0317 0.0066 1.0000 16.250 1.5153 0.05935 0.05359 -0.0316 0.0065 1.0000 16.500 1.5120 0.06270 0.05703 -0.0317 0.0063 1.0000 16.750 1.5065 0.06636 0.06077 -0.0320 0.0062 1.0000 17.000 1.4982 0.07050 0.06501 -0.0324 0.0061 1.0000 17.250 1.4926 0.07435 0.06895 -0.0329 0.0060 1.0000 17.500 1.4849 0.07855 0.07325 -0.0336 0.0060 1.0000 17.750 1.4750 0.08310 0.07790 -0.0344 0.0060 1.0000 18.000 1.4664 0.08757 0.08247 -0.0354 0.0059 1.0000 18.250 1.4551 0.09253 0.08753 -0.0366 0.0059 1.0000 18.500 1.4448 0.09737 0.09247 -0.0378 0.0058 1.0000 18.750 1.4311 0.10279 0.09800 -0.0394 0.0058 1.0000 19.000 1.4195 0.10800 0.10332 -0.0410 0.0057 1.0000