GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 50,000 Max Cl/Cd: 35.44 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe432-il-50000.txt Download as CSV file: xf-goe432-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 432 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3586 0.10306 0.09627 -0.0183 1.0000 0.1650
-7.750 -0.3641 0.10157 0.09490 -0.0180 1.0000 0.1723
-7.500 -0.3841 0.10181 0.09535 -0.0190 1.0000 0.1743
-7.250 -0.3644 0.09642 0.08993 -0.0161 1.0000 0.1861
-7.000 -0.3823 0.09651 0.09019 -0.0189 1.0000 0.1893
-6.750 -0.3670 0.09160 0.08531 -0.0150 1.0000 0.2015
-6.500 -0.3661 0.08865 0.08246 -0.0144 1.0000 0.2086
-6.250 -0.3727 0.08758 0.08149 -0.0166 1.0000 0.2189
-6.000 -0.3619 0.08338 0.07734 -0.0129 1.0000 0.2287
-5.750 -0.3618 0.08078 0.07483 -0.0129 1.0000 0.2388
-5.500 -0.3617 0.07850 0.07262 -0.0137 1.0000 0.2516
-5.250 -0.3584 0.07592 0.07011 -0.0134 1.0000 0.2661
-5.000 -0.3535 0.07298 0.06724 -0.0118 1.0000 0.2816
-4.750 -0.3480 0.07000 0.06430 -0.0092 1.0000 0.2990
-4.500 -0.3449 0.06793 0.06228 -0.0094 1.0000 0.3251
-4.250 -0.3415 0.06540 0.05982 -0.0067 1.0000 0.3546
-4.000 -0.3387 0.06256 0.05708 -0.0024 1.0000 0.3853
-3.750 -0.3366 0.05970 0.05432 0.0030 1.0000 0.4182
-3.000 -0.3457 0.05268 0.04766 0.0238 1.0000 0.5657
-2.750 -0.3482 0.05001 0.04510 0.0332 1.0000 0.6195
-2.500 -0.1273 0.03722 0.02941 -0.0420 1.0000 0.1868
-2.250 -0.0948 0.03406 0.02560 -0.0436 1.0000 0.1729
-2.000 -0.0681 0.03180 0.02297 -0.0438 1.0000 0.1709
-1.750 -0.0407 0.02980 0.02054 -0.0439 1.0000 0.1681
-1.500 -0.0148 0.02846 0.01872 -0.0437 1.0000 0.1731
-1.250 0.0100 0.02719 0.01715 -0.0434 1.0000 0.1767
-1.000 0.0314 0.02638 0.01623 -0.0427 1.0000 0.1835
-0.750 0.0517 0.02584 0.01553 -0.0420 1.0000 0.1939
-0.500 0.0736 0.02552 0.01499 -0.0416 1.0000 0.2031
-0.250 0.0941 0.02542 0.01485 -0.0414 1.0000 0.2166
0.000 0.1184 0.02554 0.01502 -0.0424 0.9975 0.2411
0.250 0.1835 0.02363 0.01474 -0.0494 0.9829 0.5048
0.500 0.2572 0.02355 0.01440 -0.0579 0.9572 1.0000
0.750 0.3146 0.02424 0.01475 -0.0641 0.9311 1.0000
1.000 0.3685 0.02470 0.01497 -0.0693 0.9064 1.0000
1.250 0.4250 0.02493 0.01503 -0.0745 0.8850 1.0000
1.500 0.4695 0.02511 0.01510 -0.0774 0.8618 1.0000
1.750 0.5239 0.02499 0.01491 -0.0816 0.8430 1.0000
2.000 0.5710 0.02483 0.01469 -0.0841 0.8231 1.0000
2.250 0.6129 0.02466 0.01450 -0.0855 0.8018 1.0000
2.500 0.6605 0.02413 0.01392 -0.0872 0.7822 1.0000
2.750 0.6922 0.02412 0.01388 -0.0866 0.7585 1.0000
3.000 0.7320 0.02370 0.01341 -0.0867 0.7370 1.0000
3.250 0.7581 0.02388 0.01356 -0.0853 0.7125 1.0000
3.500 0.7894 0.02385 0.01346 -0.0843 0.6904 1.0000
3.750 0.8141 0.02423 0.01383 -0.0830 0.6681 1.0000
4.000 0.8430 0.02450 0.01408 -0.0820 0.6484 1.0000
4.250 0.8660 0.02507 0.01467 -0.0806 0.6266 1.0000
4.500 0.8927 0.02543 0.01499 -0.0793 0.6048 1.0000
4.750 0.9154 0.02603 0.01563 -0.0777 0.5808 1.0000
5.000 0.9410 0.02655 0.01607 -0.0762 0.5564 1.0000
5.250 0.9643 0.02731 0.01680 -0.0746 0.5302 1.0000
5.500 0.9853 0.02832 0.01782 -0.0728 0.5028 1.0000
5.750 1.0064 0.02941 0.01893 -0.0711 0.4763 1.0000
6.000 1.0308 0.03035 0.01977 -0.0698 0.4533 1.0000
6.250 1.0485 0.03176 0.02135 -0.0681 0.4322 1.0000
6.500 1.0692 0.03291 0.02256 -0.0667 0.4137 1.0000
6.750 1.0909 0.03388 0.02360 -0.0653 0.3966 1.0000
7.000 1.1120 0.03493 0.02472 -0.0640 0.3810 1.0000
7.250 1.1314 0.03622 0.02615 -0.0626 0.3668 1.0000
7.500 1.1489 0.03774 0.02788 -0.0611 0.3538 1.0000
7.750 1.1650 0.03961 0.03000 -0.0597 0.3427 1.0000
8.000 1.1843 0.04119 0.03177 -0.0584 0.3317 1.0000
8.250 1.2075 0.04239 0.03301 -0.0573 0.3199 1.0000
8.500 1.2140 0.04497 0.03602 -0.0552 0.3093 1.0000
8.750 1.2223 0.04781 0.03917 -0.0533 0.3007 1.0000
9.000 1.2466 0.04921 0.04064 -0.0523 0.2904 1.0000
9.250 1.2324 0.05372 0.04566 -0.0494 0.2832 1.0000
9.500 1.2455 0.05587 0.04802 -0.0478 0.2733 1.0000
9.750 1.2243 0.06114 0.05362 -0.0452 0.2684 1.0000
10.000 1.2293 0.06354 0.05619 -0.0432 0.2581 1.0000
10.250 1.1849 0.07119 0.06399 -0.0415 0.2592 1.0000
10.500 1.1392 0.07954 0.07228 -0.0413 0.2612 1.0000
10.750 1.3430 0.05573 0.04765 -0.0368 0.1624 1.0000
11.000 1.2181 0.07235 0.06552 -0.0333 0.2107 1.0000
11.250 1.1916 0.07798 0.07121 -0.0325 0.2081 1.0000
11.500 1.1639 0.08494 0.07819 -0.0334 0.2064 1.0000
11.750 1.2536 0.07267 0.06579 -0.0242 0.1428 1.0000
12.000 1.2201 0.07897 0.07225 -0.0241 0.1453 1.0000
12.250 1.1885 0.08624 0.07959 -0.0260 0.1473 1.0000
12.500 1.1585 0.09470 0.08809 -0.0293 0.1486 1.0000
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Polar data table (+)
Polar graphs
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