GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 200,000 Max Cl/Cd: 67.59 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe199-il-200000-n5.txt Download as CSV file: xf-goe199-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3192 0.09872 0.09539 -0.0237 1.0000 0.0211
-7.750 -0.3173 0.09609 0.09282 -0.0256 1.0000 0.0211
-7.500 -0.3147 0.09343 0.09022 -0.0276 1.0000 0.0211
-7.250 -0.3003 0.08970 0.08649 -0.0330 0.9950 0.0212
-7.000 -0.2810 0.08497 0.08176 -0.0366 0.9876 0.0213
-6.750 -0.2645 0.08098 0.07777 -0.0377 0.9803 0.0217
-6.500 -0.2422 0.07731 0.07406 -0.0420 0.9712 0.0228
-6.250 -0.2137 0.07332 0.07001 -0.0488 0.9607 0.0249
-6.000 -0.1735 0.06879 0.06535 -0.0600 0.9487 0.0257
-5.750 -0.1396 0.06443 0.06082 -0.0672 0.9369 0.0258
-5.250 -0.1044 0.05706 0.05338 -0.0695 0.9154 0.0267
-5.000 -0.0832 0.05434 0.05059 -0.0711 0.9046 0.0281
-4.750 -0.0553 0.05119 0.04732 -0.0743 0.8953 0.0298
-4.500 -0.0067 0.04791 0.04360 -0.0807 0.8873 0.0319
-4.000 0.0338 0.04152 0.03710 -0.0825 0.8708 0.0337
-3.750 0.0595 0.03926 0.03473 -0.0837 0.8622 0.0354
-3.500 0.0901 0.03688 0.03211 -0.0852 0.8550 0.0380
-3.250 0.1296 0.03422 0.02895 -0.0872 0.8473 0.0407
-3.000 0.1506 0.03189 0.02664 -0.0877 0.8401 0.0422
-2.750 0.1770 0.03032 0.02496 -0.0883 0.8317 0.0455
-2.500 0.2124 0.02856 0.02267 -0.0890 0.8249 0.0508
-2.250 0.2375 0.02661 0.02071 -0.0896 0.8163 0.0524
-2.000 0.2700 0.02694 0.02054 -0.0893 0.8077 0.0607
-1.750 0.2950 0.02398 0.01755 -0.0898 0.7957 0.0625
-1.250 0.3549 0.02141 0.01412 -0.0887 0.7623 0.0504
-1.000 0.3838 0.01926 0.01170 -0.0884 0.7469 0.0396
-0.750 0.4119 0.01807 0.01029 -0.0883 0.7325 0.0387
-0.500 0.4403 0.01716 0.00917 -0.0882 0.7179 0.0382
-0.250 0.4685 0.01658 0.00836 -0.0879 0.7024 0.0391
0.000 0.4966 0.01609 0.00767 -0.0877 0.6857 0.0398
0.250 0.5245 0.01542 0.00686 -0.0875 0.6675 0.0393
0.500 0.5521 0.01490 0.00621 -0.0873 0.6469 0.0390
0.750 0.5795 0.01450 0.00566 -0.0871 0.6249 0.0389
1.000 0.6066 0.01418 0.00522 -0.0868 0.5997 0.0389
1.250 0.6334 0.01397 0.00486 -0.0865 0.5734 0.0391
1.500 0.6599 0.01385 0.00459 -0.0862 0.5478 0.0395
1.750 0.6865 0.01379 0.00442 -0.0859 0.5236 0.0399
2.000 0.7130 0.01371 0.00425 -0.0858 0.5009 0.0421
2.250 0.7397 0.01374 0.00420 -0.0857 0.4779 0.0441
2.500 0.7664 0.01384 0.00418 -0.0855 0.4546 0.0449
2.750 0.7930 0.01398 0.00420 -0.0853 0.4288 0.0460
3.000 0.8193 0.01417 0.00425 -0.0851 0.4008 0.0475
3.250 0.8452 0.01443 0.00434 -0.0849 0.3727 0.0498
3.500 0.8710 0.01471 0.00452 -0.0847 0.3478 0.0562
4.000 0.9224 0.01375 0.00498 -0.0844 0.3099 1.0000
4.250 0.9481 0.01411 0.00523 -0.0842 0.2957 1.0000
4.500 0.9737 0.01448 0.00551 -0.0839 0.2839 1.0000
4.750 0.9991 0.01485 0.00580 -0.0837 0.2738 1.0000
5.000 1.0248 0.01518 0.00612 -0.0835 0.2654 1.0000
5.250 1.0499 0.01558 0.00645 -0.0832 0.2581 1.0000
5.500 1.0754 0.01591 0.00680 -0.0829 0.2517 1.0000
5.750 1.1004 0.01629 0.00716 -0.0826 0.2457 1.0000
6.000 1.1252 0.01669 0.00756 -0.0823 0.2405 1.0000
6.250 1.1503 0.01704 0.00795 -0.0820 0.2355 1.0000
6.500 1.1749 0.01744 0.00837 -0.0816 0.2313 1.0000
6.750 1.1989 0.01787 0.00883 -0.0812 0.2268 1.0000
7.000 1.2238 0.01821 0.00925 -0.0808 0.2214 1.0000
7.250 1.2476 0.01862 0.00969 -0.0804 0.2158 1.0000
7.500 1.2713 0.01905 0.01016 -0.0799 0.2112 1.0000
7.750 1.2955 0.01939 0.01063 -0.0795 0.2051 1.0000
8.000 1.3179 0.01985 0.01110 -0.0789 0.1974 1.0000
8.250 1.3414 0.02018 0.01153 -0.0784 0.1869 1.0000
8.500 1.3641 0.02058 0.01200 -0.0779 0.1757 1.0000
8.750 1.3859 0.02105 0.01252 -0.0772 0.1590 1.0000
9.000 1.3989 0.02239 0.01339 -0.0755 0.0852 1.0000
9.250 1.4063 0.02441 0.01517 -0.0730 0.0438 1.0000
9.500 1.4192 0.02571 0.01649 -0.0711 0.0338 1.0000
9.750 1.4304 0.02702 0.01789 -0.0690 0.0286 1.0000
10.000 1.4429 0.02806 0.01911 -0.0670 0.0255 1.0000
10.250 1.4506 0.02932 0.02052 -0.0644 0.0233 1.0000
10.500 1.4504 0.03094 0.02228 -0.0608 0.0216 1.0000
10.750 1.4546 0.03236 0.02386 -0.0581 0.0204 1.0000
11.000 1.4583 0.03394 0.02559 -0.0557 0.0191 1.0000
11.250 1.4607 0.03574 0.02753 -0.0535 0.0179 1.0000
11.500 1.4612 0.03782 0.02975 -0.0516 0.0170 1.0000
11.750 1.4585 0.04036 0.03244 -0.0498 0.0164 1.0000
12.000 1.4518 0.04348 0.03569 -0.0484 0.0158 1.0000
12.250 1.4427 0.04709 0.03943 -0.0473 0.0154 1.0000
12.500 1.4390 0.05031 0.04282 -0.0466 0.0151 1.0000
12.750 1.4341 0.05382 0.04649 -0.0463 0.0147 1.0000
13.000 1.4284 0.05756 0.05039 -0.0462 0.0144 1.0000
13.250 1.4225 0.06149 0.05447 -0.0464 0.0139 1.0000
13.500 1.4161 0.06563 0.05876 -0.0468 0.0135 1.0000
13.750 1.4096 0.06991 0.06317 -0.0475 0.0132 1.0000
14.000 1.4029 0.07433 0.06772 -0.0484 0.0128 1.0000
14.250 1.3965 0.07889 0.07240 -0.0495 0.0124 1.0000
14.500 1.3895 0.08359 0.07723 -0.0507 0.0121 1.0000
14.750 1.3824 0.08834 0.08209 -0.0520 0.0119 1.0000
15.000 1.3755 0.09308 0.08692 -0.0533 0.0117 1.0000
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Polar data table (+)
Polar graphs
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