GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 200,000 Max Cl/Cd: 71.96 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe199-il-200000.txt Download as CSV file: xf-goe199-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3203 0.08968 0.08643 -0.0232 1.0000 0.0273
-7.000 -0.3165 0.08709 0.08390 -0.0239 1.0000 0.0279
-6.750 -0.3183 0.08507 0.08194 -0.0235 1.0000 0.0284
-6.500 -0.3284 0.08385 0.08079 -0.0211 1.0000 0.0286
-6.250 -0.3376 0.08257 0.07956 -0.0192 0.9999 0.0290
-6.000 -0.3006 0.07766 0.07457 -0.0284 0.9952 0.0304
-5.750 -0.2296 0.07300 0.06960 -0.0490 0.9885 0.0318
-5.500 -0.2121 0.06714 0.06380 -0.0505 0.9851 0.0323
-5.250 -0.1891 0.06314 0.05980 -0.0527 0.9814 0.0333
-5.000 -0.1568 0.05945 0.05605 -0.0576 0.9761 0.0353
-4.750 -0.0949 0.05586 0.05211 -0.0691 0.9725 0.0390
-4.500 -0.0555 0.05054 0.04665 -0.0754 0.9702 0.0400
-4.250 -0.0314 0.04716 0.04328 -0.0773 0.9640 0.0412
-4.000 0.0034 0.04416 0.04019 -0.0811 0.9595 0.0440
-3.750 0.0599 0.04136 0.03686 -0.0876 0.9560 0.0495
-3.500 0.0825 0.03794 0.03351 -0.0890 0.9484 0.0509
-3.250 0.1135 0.03558 0.03108 -0.0911 0.9427 0.0538
-3.000 0.1573 0.03472 0.02961 -0.0932 0.9354 0.0608
-2.750 0.1795 0.03117 0.02621 -0.0942 0.9278 0.0631
-2.500 0.2059 0.02962 0.02457 -0.0946 0.9192 0.0683
-2.250 0.2375 0.02793 0.02254 -0.0949 0.9111 0.0752
-2.000 0.2605 0.02635 0.02093 -0.0943 0.8992 0.0793
-1.750 0.2870 0.02511 0.01936 -0.0933 0.8856 0.0889
-1.500 0.3094 0.02384 0.01801 -0.0921 0.8706 0.0960
-1.250 0.3341 0.02255 0.01655 -0.0912 0.8568 0.1076
-1.000 0.3592 0.02159 0.01545 -0.0905 0.8443 0.1253
-0.750 0.3840 0.02054 0.01427 -0.0901 0.8328 0.1516
-0.500 0.4091 0.01954 0.01323 -0.0898 0.8197 0.1826
-0.250 0.4344 0.01861 0.01221 -0.0895 0.8067 0.2237
0.000 0.4600 0.01745 0.01105 -0.0891 0.7939 0.2576
0.250 0.4880 0.01666 0.01013 -0.0885 0.7810 0.2785
0.500 0.5311 0.01602 0.00837 -0.0859 0.7700 0.0840
0.750 0.5589 0.01518 0.00738 -0.0852 0.7561 0.0781
1.000 0.5869 0.01517 0.00715 -0.0844 0.7403 0.0732
1.250 0.6140 0.01427 0.00625 -0.0839 0.7235 0.0704
1.500 0.6411 0.01379 0.00574 -0.0834 0.7050 0.0685
1.750 0.6681 0.01343 0.00534 -0.0829 0.6854 0.0676
2.000 0.6950 0.01316 0.00502 -0.0824 0.6647 0.0678
2.250 0.7219 0.01297 0.00479 -0.0820 0.6401 0.0692
2.500 0.7486 0.01291 0.00462 -0.0816 0.6132 0.0727
2.750 0.7750 0.01287 0.00443 -0.0811 0.5840 0.0793
3.000 0.8012 0.01300 0.00438 -0.0806 0.5536 0.0872
3.250 0.8275 0.01150 0.00441 -0.0804 0.5232 1.0000
3.500 0.8531 0.01188 0.00451 -0.0799 0.4903 1.0000
3.750 0.8783 0.01231 0.00468 -0.0795 0.4533 1.0000
4.000 0.9031 0.01277 0.00491 -0.0790 0.4119 1.0000
4.250 0.9275 0.01332 0.00518 -0.0785 0.3762 1.0000
4.500 0.9520 0.01387 0.00552 -0.0781 0.3497 1.0000
4.750 0.9766 0.01444 0.00590 -0.0778 0.3314 1.0000
5.000 1.0015 0.01497 0.00633 -0.0774 0.3178 1.0000
5.250 1.0271 0.01543 0.00674 -0.0771 0.3069 1.0000
5.500 1.0523 0.01595 0.00720 -0.0768 0.2987 1.0000
5.750 1.0779 0.01641 0.00764 -0.0766 0.2916 1.0000
6.000 1.1032 0.01698 0.00816 -0.0763 0.2858 1.0000
6.250 1.1289 0.01738 0.00862 -0.0761 0.2795 1.0000
6.500 1.1539 0.01790 0.00907 -0.0758 0.2731 1.0000
6.750 1.1792 0.01826 0.00955 -0.0755 0.2663 1.0000
7.000 1.2038 0.01868 0.00996 -0.0752 0.2594 1.0000
7.250 1.2284 0.01907 0.01044 -0.0749 0.2527 1.0000
7.500 1.2527 0.01942 0.01084 -0.0745 0.2459 1.0000
7.750 1.2767 0.01985 0.01136 -0.0741 0.2393 1.0000
8.000 1.2999 0.02011 0.01170 -0.0735 0.2303 1.0000
8.250 1.3227 0.02036 0.01208 -0.0730 0.2199 1.0000
8.500 1.3449 0.02057 0.01241 -0.0723 0.2070 1.0000
8.750 1.3661 0.02077 0.01267 -0.0715 0.1836 1.0000
9.000 1.3732 0.02284 0.01401 -0.0691 0.0681 1.0000
9.250 1.3838 0.02466 0.01578 -0.0667 0.0497 1.0000
9.500 1.3969 0.02598 0.01724 -0.0647 0.0442 1.0000
9.750 1.4049 0.02752 0.01889 -0.0621 0.0406 1.0000
10.000 1.4066 0.02927 0.02077 -0.0586 0.0383 1.0000
10.250 1.4097 0.03067 0.02233 -0.0553 0.0365 1.0000
10.500 1.4097 0.03236 0.02414 -0.0519 0.0350 1.0000
10.750 1.4089 0.03432 0.02619 -0.0490 0.0338 1.0000
11.000 1.4075 0.03653 0.02849 -0.0464 0.0328 1.0000
11.250 1.4053 0.03901 0.03105 -0.0440 0.0319 1.0000
11.500 1.4028 0.04183 0.03392 -0.0417 0.0310 1.0000
11.750 1.4055 0.04449 0.03663 -0.0396 0.0301 1.0000
12.000 1.4114 0.04650 0.03881 -0.0383 0.0293 1.0000
12.250 1.4168 0.04870 0.04117 -0.0370 0.0283 1.0000
12.500 1.4230 0.05101 0.04361 -0.0356 0.0276 1.0000
12.750 1.4296 0.05342 0.04616 -0.0342 0.0270 1.0000
13.000 1.4361 0.05594 0.04883 -0.0329 0.0265 1.0000
13.250 1.4420 0.05863 0.05167 -0.0317 0.0261 1.0000
13.500 1.4464 0.06154 0.05476 -0.0305 0.0258 1.0000
13.750 1.4490 0.06465 0.05802 -0.0296 0.0254 1.0000
14.000 1.4480 0.06800 0.06156 -0.0289 0.0250 1.0000
14.250 1.4463 0.07154 0.06523 -0.0284 0.0245 1.0000
14.500 1.4445 0.07550 0.06933 -0.0279 0.0240 1.0000
14.750 1.4383 0.08018 0.07420 -0.0277 0.0237 1.0000
15.000 1.4268 0.08509 0.07933 -0.0280 0.0236 1.0000
15.250 1.4133 0.08997 0.08443 -0.0291 0.0237 1.0000
15.500 1.3981 0.09514 0.08983 -0.0308 0.0238 1.0000
15.750 1.3813 0.10078 0.09570 -0.0332 0.0239 1.0000
16.000 1.3632 0.10712 0.10228 -0.0364 0.0241 1.0000
16.250 1.3423 0.11455 0.10998 -0.0408 0.0245 1.0000
16.500 1.3087 0.12531 0.12108 -0.0483 0.0251 1.0000
16.750 1.2742 0.13769 0.13378 -0.0571 0.0258 1.0000
17.000 1.2425 0.15063 0.14694 -0.0663 0.0267 1.0000
17.250 1.2101 0.16494 0.16143 -0.0762 0.0280 1.0000
17.500 1.1849 0.17795 0.17453 -0.0846 0.0293 1.0000
17.750 1.1816 0.18378 0.18036 -0.0865 0.0304 1.0000
18.000 0.8468 0.18285 0.17967 -0.0655 0.0385 1.0000
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Polar data table (+)
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