GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 500,000 Max Cl/Cd: 101.71 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe532-il-500000.txt Download as CSV file: xf-goe532-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2876 0.09998 0.09760 -0.0348 1.0000 0.0328
-9.750 -0.2854 0.09705 0.09470 -0.0355 1.0000 0.0337
-9.500 -0.3205 0.08768 0.08538 -0.0438 1.0000 0.0355
-9.250 -0.3160 0.08556 0.08329 -0.0420 1.0000 0.0358
-9.000 -0.3122 0.08392 0.08169 -0.0405 1.0000 0.0359
-8.750 -0.3094 0.08264 0.08046 -0.0387 1.0000 0.0362
-8.500 -0.2863 0.07967 0.07749 -0.0425 0.9967 0.0368
-8.250 -0.2951 0.05493 0.05241 -0.0855 0.9680 0.0407
-8.000 -0.2727 0.05190 0.04952 -0.0858 0.9608 0.0411
-7.750 -0.2423 0.05037 0.04801 -0.0883 0.9533 0.0415
-7.500 -0.2113 0.04764 0.04523 -0.0933 0.9417 0.0421
-7.250 -0.1976 0.03902 0.03566 -0.1054 0.9144 0.0465
-7.000 -0.1813 0.03408 0.03063 -0.1070 0.8965 0.0474
-6.750 -0.1588 0.03257 0.02908 -0.1071 0.8789 0.0480
-6.500 -0.1378 0.03112 0.02752 -0.1070 0.8614 0.0487
-6.250 -0.1176 0.02948 0.02568 -0.1068 0.8442 0.0500
-6.000 -0.1015 0.02661 0.02211 -0.1065 0.8269 0.0543
-5.750 -0.0789 0.02508 0.02055 -0.1061 0.8099 0.0551
-5.500 -0.0560 0.02394 0.01930 -0.1056 0.7911 0.0562
-5.250 -0.0363 0.01797 0.01194 -0.1036 0.7744 0.0408
-5.000 -0.0114 0.01707 0.01083 -0.1028 0.7520 0.0406
-4.750 0.0131 0.01604 0.00960 -0.1020 0.7277 0.0406
-4.250 0.0623 0.01434 0.00747 -0.1003 0.6753 0.0410
-4.000 0.0872 0.01360 0.00663 -0.0997 0.6533 0.0417
-3.750 0.1128 0.01321 0.00613 -0.0990 0.6345 0.0424
-3.500 0.1388 0.01284 0.00566 -0.0984 0.6190 0.0429
-3.250 0.1648 0.01251 0.00523 -0.0978 0.6047 0.0435
-3.000 0.1911 0.01220 0.00485 -0.0973 0.5908 0.0441
-2.750 0.2177 0.01192 0.00450 -0.0968 0.5778 0.0448
-2.500 0.2442 0.01170 0.00420 -0.0963 0.5666 0.0456
-2.250 0.2711 0.01151 0.00394 -0.0958 0.5564 0.0464
-2.000 0.2976 0.01116 0.00357 -0.0954 0.5477 0.0479
-1.750 0.3245 0.01098 0.00337 -0.0950 0.5389 0.0496
-1.500 0.3516 0.01085 0.00320 -0.0946 0.5313 0.0513
-1.250 0.3791 0.01074 0.00305 -0.0943 0.5236 0.0530
-1.000 0.4059 0.01059 0.00285 -0.0939 0.5163 0.0559
-0.750 0.4336 0.01047 0.00273 -0.0936 0.5088 0.0600
-0.500 0.4608 0.01037 0.00260 -0.0933 0.5020 0.0690
-0.250 0.4857 0.00953 0.00251 -0.0930 0.4962 0.3011
0.000 0.5118 0.00922 0.00258 -0.0927 0.4904 0.4341
0.250 0.5380 0.00911 0.00264 -0.0922 0.4849 0.5114
0.500 0.5641 0.00900 0.00272 -0.0917 0.4798 0.5850
0.750 0.5899 0.00886 0.00281 -0.0910 0.4740 0.6632
1.000 0.6146 0.00876 0.00288 -0.0901 0.4684 0.7367
1.250 0.6580 0.00832 0.00292 -0.0929 0.4625 1.0000
1.500 0.6856 0.00840 0.00296 -0.0926 0.4571 1.0000
1.750 0.7126 0.00852 0.00300 -0.0923 0.4510 1.0000
2.000 0.7396 0.00864 0.00305 -0.0919 0.4444 1.0000
2.250 0.7667 0.00873 0.00309 -0.0916 0.4366 1.0000
2.500 0.7932 0.00888 0.00316 -0.0911 0.4291 1.0000
2.750 0.8206 0.00896 0.00322 -0.0909 0.4224 1.0000
3.000 0.8472 0.00910 0.00330 -0.0905 0.4159 1.0000
3.250 0.8742 0.00922 0.00340 -0.0901 0.4099 1.0000
3.500 0.9011 0.00933 0.00348 -0.0898 0.4024 1.0000
3.750 0.9274 0.00948 0.00358 -0.0894 0.3944 1.0000
4.000 0.9540 0.00960 0.00368 -0.0890 0.3845 1.0000
4.250 0.9803 0.00975 0.00379 -0.0886 0.3740 1.0000
4.500 1.0060 0.00993 0.00391 -0.0881 0.3606 1.0000
4.750 1.0313 0.01014 0.00405 -0.0875 0.3404 1.0000
5.000 1.0535 0.01058 0.00426 -0.0866 0.2995 1.0000
5.250 1.0721 0.01135 0.00470 -0.0851 0.2459 1.0000
5.500 1.0931 0.01192 0.00511 -0.0840 0.2232 1.0000
5.750 1.1161 0.01233 0.00544 -0.0832 0.2125 1.0000
6.000 1.1395 0.01268 0.00576 -0.0824 0.2060 1.0000
6.250 1.1631 0.01300 0.00606 -0.0816 0.2010 1.0000
6.500 1.1859 0.01336 0.00639 -0.0808 0.1966 1.0000
6.750 1.2088 0.01370 0.00673 -0.0799 0.1926 1.0000
7.000 1.2326 0.01397 0.00701 -0.0792 0.1895 1.0000
7.250 1.2555 0.01428 0.00733 -0.0784 0.1862 1.0000
7.500 1.2775 0.01463 0.00769 -0.0775 0.1830 1.0000
7.750 1.2983 0.01505 0.00809 -0.0764 0.1795 1.0000
8.000 1.3205 0.01536 0.00843 -0.0754 0.1769 1.0000
8.250 1.3433 0.01561 0.00874 -0.0746 0.1740 1.0000
8.500 1.3647 0.01594 0.00909 -0.0736 0.1704 1.0000
8.750 1.3836 0.01638 0.00951 -0.0723 0.1658 1.0000
9.000 1.4031 0.01676 0.00992 -0.0710 0.1620 1.0000
9.250 1.4243 0.01700 0.01022 -0.0699 0.1581 1.0000
9.500 1.4416 0.01738 0.01060 -0.0682 0.1531 1.0000
9.750 1.4567 0.01784 0.01107 -0.0662 0.1479 1.0000
10.000 1.4758 0.01814 0.01140 -0.0649 0.1397 1.0000
10.250 1.4912 0.01861 0.01185 -0.0631 0.1281 1.0000
10.750 1.5047 0.02047 0.01345 -0.0576 0.0955 1.0000
11.000 1.5106 0.02151 0.01447 -0.0549 0.0910 1.0000
11.250 1.5182 0.02250 0.01552 -0.0527 0.0889 1.0000
11.500 1.5245 0.02365 0.01672 -0.0505 0.0871 1.0000
11.750 1.5290 0.02498 0.01811 -0.0484 0.0856 1.0000
12.000 1.5315 0.02656 0.01974 -0.0464 0.0841 1.0000
12.250 1.5321 0.02840 0.02164 -0.0446 0.0825 1.0000
12.500 1.5310 0.03051 0.02381 -0.0430 0.0810 1.0000
12.750 1.5344 0.03239 0.02577 -0.0418 0.0801 1.0000
13.000 1.5395 0.03421 0.02769 -0.0410 0.0793 1.0000
13.250 1.5429 0.03627 0.02985 -0.0402 0.0785 1.0000
13.500 1.5454 0.03851 0.03218 -0.0396 0.0777 1.0000
13.750 1.5466 0.04096 0.03471 -0.0391 0.0767 1.0000
14.000 1.5473 0.04352 0.03736 -0.0388 0.0758 1.0000
14.250 1.5473 0.04621 0.04013 -0.0385 0.0749 1.0000
14.500 1.5459 0.04910 0.04308 -0.0384 0.0739 1.0000
14.750 1.5426 0.05222 0.04625 -0.0383 0.0727 1.0000
15.000 1.5379 0.05540 0.04946 -0.0380 0.0712 1.0000
15.250 1.5406 0.05800 0.05215 -0.0381 0.0704 1.0000
15.500 1.5445 0.06060 0.05486 -0.0385 0.0696 1.0000
15.750 1.5475 0.06331 0.05767 -0.0389 0.0686 1.0000
16.000 1.5495 0.06619 0.06064 -0.0394 0.0674 1.0000
16.250 1.5507 0.06917 0.06370 -0.0399 0.0663 1.0000
16.500 1.5521 0.07215 0.06675 -0.0405 0.0654 1.0000
16.750 1.5529 0.07524 0.06989 -0.0411 0.0645 1.0000
17.000 1.5526 0.07844 0.07313 -0.0417 0.0634 1.0000
17.250 1.5546 0.08109 0.07579 -0.0419 0.0623 1.0000
17.500 1.5567 0.08408 0.07888 -0.0426 0.0616 1.0000
17.750 1.5572 0.08755 0.08247 -0.0438 0.0609 1.0000
18.000 1.5578 0.09099 0.08603 -0.0450 0.0601 1.0000
18.250 1.5580 0.09450 0.08964 -0.0462 0.0592 1.0000
18.500 1.5581 0.09804 0.09327 -0.0475 0.0583 1.0000
18.750 1.5581 0.10161 0.09692 -0.0489 0.0573 1.0000
19.000 1.5571 0.10542 0.10080 -0.0504 0.0564 1.0000
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