GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 200,000 Max Cl/Cd: 69.27 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe509-il-200000.txt Download as CSV file: xf-goe509-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3075 0.10729 0.10392 -0.0313 1.0000 0.0433
-9.250 -0.3094 0.10491 0.10158 -0.0308 1.0000 0.0442
-9.000 -0.3136 0.10253 0.09925 -0.0303 1.0000 0.0453
-8.750 -0.2573 0.09024 0.08734 -0.0411 0.9922 0.0488
-8.500 -0.2274 0.08638 0.08346 -0.0400 0.9895 0.0505
-8.250 -0.2118 0.08207 0.07913 -0.0431 0.9860 0.0524
-8.000 -0.2003 0.07747 0.07453 -0.0474 0.9824 0.0543
-7.750 -0.3321 0.08711 0.08409 -0.0406 0.9876 0.0497
-7.500 -0.3077 0.08358 0.08055 -0.0435 0.9840 0.0513
-7.250 -0.2882 0.07938 0.07632 -0.0489 0.9757 0.0532
-7.000 -0.2661 0.07405 0.07090 -0.0581 0.9660 0.0568
-6.750 -0.2434 0.06560 0.06223 -0.0708 0.9579 0.0592
-6.500 -0.2292 0.06298 0.05963 -0.0698 0.9491 0.0602
-6.250 -0.2022 0.06012 0.05675 -0.0719 0.9454 0.0625
-6.000 -0.1813 0.05631 0.05276 -0.0756 0.9347 0.0690
-5.750 -0.1583 0.05003 0.04624 -0.0803 0.9298 0.0725
-5.500 -0.1433 0.04843 0.04466 -0.0788 0.9197 0.0745
-5.250 -0.1132 0.04518 0.04126 -0.0814 0.9157 0.0799
-5.000 -0.1036 0.04041 0.03608 -0.0808 0.9042 0.0867
-4.750 -0.0717 0.03842 0.03409 -0.0823 0.9010 0.0906
-4.500 -0.0591 0.03536 0.03064 -0.0806 0.8903 0.1019
-4.250 -0.0428 0.02563 0.01915 -0.0760 0.8855 0.0586
-4.000 -0.0262 0.02273 0.01595 -0.0740 0.8756 0.0600
-3.750 0.0104 0.02116 0.01429 -0.0756 0.8715 0.0633
-3.500 0.0362 0.01983 0.01270 -0.0746 0.8627 0.0650
-3.250 0.0735 0.01875 0.01133 -0.0759 0.8575 0.0689
-3.000 0.1041 0.01784 0.01017 -0.0759 0.8492 0.0708
-2.750 0.1414 0.01633 0.00860 -0.0776 0.8428 0.0754
-2.500 0.1731 0.01567 0.00787 -0.0780 0.8336 0.0798
-2.250 0.2107 0.01503 0.00707 -0.0795 0.8256 0.0840
-2.000 0.2379 0.01423 0.00632 -0.0792 0.8143 0.0906
-1.750 0.2674 0.01381 0.00584 -0.0791 0.8035 0.0978
-1.500 0.2966 0.01327 0.00531 -0.0791 0.7931 0.1090
-1.250 0.3185 0.01292 0.00500 -0.0776 0.7805 0.1265
-1.000 0.3392 0.01232 0.00487 -0.0760 0.7683 0.2238
-0.750 0.3634 0.01232 0.00496 -0.0749 0.7555 0.3213
-0.500 0.3872 0.01225 0.00487 -0.0737 0.7418 0.3542
-0.250 0.4099 0.01213 0.00474 -0.0724 0.7267 0.3811
0.000 0.4305 0.01195 0.00460 -0.0706 0.7099 0.4069
0.250 0.4489 0.01172 0.00445 -0.0684 0.6915 0.4406
0.500 0.6612 0.01121 0.00489 -0.1066 0.6412 0.9980
0.750 0.6880 0.01132 0.00476 -0.1063 0.6131 1.0000
1.000 0.7070 0.01149 0.00474 -0.1044 0.5883 1.0000
1.250 0.7262 0.01169 0.00473 -0.1026 0.5670 1.0000
1.500 0.7457 0.01188 0.00476 -0.1009 0.5486 1.0000
1.750 0.7660 0.01208 0.00481 -0.0994 0.5344 1.0000
2.000 0.7865 0.01230 0.00488 -0.0980 0.5226 1.0000
2.250 0.8072 0.01249 0.00498 -0.0965 0.5111 1.0000
2.500 0.8281 0.01271 0.00509 -0.0952 0.5014 1.0000
2.750 0.8491 0.01295 0.00522 -0.0939 0.4923 1.0000
3.000 0.8703 0.01316 0.00538 -0.0926 0.4835 1.0000
3.250 0.8920 0.01343 0.00553 -0.0914 0.4760 1.0000
3.500 0.9136 0.01364 0.00573 -0.0902 0.4689 1.0000
3.750 0.9354 0.01391 0.00594 -0.0891 0.4620 1.0000
4.000 0.9576 0.01418 0.00617 -0.0880 0.4558 1.0000
4.250 0.9790 0.01442 0.00641 -0.0868 0.4491 1.0000
4.500 1.0026 0.01477 0.00665 -0.0861 0.4433 1.0000
4.750 1.0230 0.01499 0.00696 -0.0847 0.4370 1.0000
5.000 1.0446 0.01527 0.00722 -0.0835 0.4307 1.0000
5.250 1.0671 0.01561 0.00753 -0.0826 0.4247 1.0000
5.500 1.0863 0.01584 0.00783 -0.0809 0.4172 1.0000
5.750 1.1078 0.01618 0.00811 -0.0798 0.4094 1.0000
6.000 1.1249 0.01637 0.00840 -0.0777 0.4010 1.0000
6.250 1.1450 0.01668 0.00865 -0.0763 0.3930 1.0000
6.500 1.1603 0.01684 0.00893 -0.0739 0.3835 1.0000
6.750 1.1772 0.01707 0.00917 -0.0718 0.3744 1.0000
7.000 1.1920 0.01723 0.00938 -0.0694 0.3644 1.0000
7.250 1.2066 0.01742 0.00964 -0.0668 0.3540 1.0000
7.500 1.2208 0.01763 0.00987 -0.0643 0.3440 1.0000
7.750 1.2341 0.01784 0.01014 -0.0615 0.3327 1.0000
8.000 1.2469 0.01807 0.01044 -0.0587 0.3204 1.0000
8.250 1.2580 0.01835 0.01074 -0.0556 0.3071 1.0000
8.500 1.2664 0.01866 0.01105 -0.0521 0.2939 1.0000
8.750 1.2733 0.01902 0.01140 -0.0483 0.2812 1.0000
9.000 1.2806 0.01947 0.01181 -0.0447 0.2696 1.0000
9.250 1.2890 0.01997 0.01229 -0.0415 0.2580 1.0000
9.500 1.2987 0.02050 0.01284 -0.0386 0.2474 1.0000
9.750 1.3079 0.02111 0.01345 -0.0357 0.2380 1.0000
10.000 1.3164 0.02177 0.01410 -0.0328 0.2288 1.0000
10.250 1.3271 0.02239 0.01478 -0.0304 0.2201 1.0000
10.500 1.3346 0.02318 0.01554 -0.0276 0.2121 1.0000
10.750 1.3451 0.02387 0.01632 -0.0254 0.2033 1.0000
11.000 1.3528 0.02472 0.01721 -0.0229 0.1948 1.0000
11.250 1.3584 0.02571 0.01821 -0.0203 0.1848 1.0000
11.500 1.3660 0.02666 0.01923 -0.0180 0.1739 1.0000
11.750 1.3710 0.02783 0.02044 -0.0157 0.1608 1.0000
12.000 1.3746 0.02917 0.02179 -0.0134 0.1439 1.0000
12.250 1.3716 0.03111 0.02357 -0.0110 0.1009 1.0000
12.500 1.3561 0.03418 0.02638 -0.0081 0.0767 1.0000
12.750 1.3458 0.03709 0.02927 -0.0058 0.0606 1.0000
13.000 1.3387 0.03987 0.03206 -0.0042 0.0530 1.0000
13.250 1.3322 0.04276 0.03500 -0.0029 0.0491 1.0000
13.500 1.3253 0.04585 0.03819 -0.0019 0.0467 1.0000
13.750 1.3160 0.04938 0.04181 -0.0012 0.0449 1.0000
14.000 1.3050 0.05328 0.04583 -0.0009 0.0436 1.0000
14.250 1.2927 0.05755 0.05023 -0.0010 0.0427 1.0000
14.500 1.2827 0.06176 0.05458 -0.0013 0.0418 1.0000
14.750 1.2723 0.06616 0.05913 -0.0018 0.0410 1.0000
15.000 1.2614 0.07078 0.06387 -0.0026 0.0400 1.0000
15.250 1.2526 0.07515 0.06836 -0.0034 0.0396 1.0000
15.500 1.2430 0.07967 0.07296 -0.0042 0.0386 1.0000
15.750 1.2338 0.08404 0.07738 -0.0049 0.0376 1.0000
16.000 1.2278 0.08780 0.08115 -0.0053 0.0365 1.0000
16.250 1.2287 0.09005 0.08337 -0.0045 0.0355 1.0000
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