GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 100,000 Max Cl/Cd: 58.58 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe546-il-100000-n5.txt Download as CSV file: xf-goe546-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 546 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4737 0.07369 0.06902 -0.0465 1.0000 0.0369
-8.000 -0.4907 0.06865 0.06400 -0.0482 1.0000 0.0368
-7.500 -0.4694 0.06124 0.05648 -0.0551 0.9918 0.0390
-7.250 -0.4523 0.05458 0.04954 -0.0626 0.9849 0.0401
-7.000 -0.4368 0.04765 0.04215 -0.0684 0.9773 0.0405
-6.750 -0.4176 0.04252 0.03652 -0.0719 0.9708 0.0418
-6.500 -0.3931 0.03800 0.03133 -0.0750 0.9653 0.0444
-6.250 -0.3697 0.03436 0.02694 -0.0763 0.9592 0.0458
-6.000 -0.3429 0.03158 0.02372 -0.0777 0.9543 0.0472
-5.750 -0.3109 0.03015 0.02218 -0.0796 0.9511 0.0497
-5.500 -0.2866 0.02865 0.02041 -0.0796 0.9445 0.0516
-5.250 -0.2554 0.02689 0.01825 -0.0807 0.9402 0.0532
-5.000 -0.2206 0.02551 0.01648 -0.0823 0.9372 0.0558
-4.750 -0.1950 0.02444 0.01513 -0.0820 0.9305 0.0578
-4.500 -0.1635 0.02311 0.01374 -0.0830 0.9262 0.0596
-4.250 -0.1284 0.02209 0.01264 -0.0845 0.9231 0.0616
-4.000 -0.1004 0.02136 0.01183 -0.0846 0.9172 0.0643
-3.750 -0.0687 0.02071 0.01107 -0.0854 0.9120 0.0683
-3.500 -0.0335 0.01990 0.01020 -0.0868 0.9086 0.0713
-3.250 -0.0036 0.01923 0.00956 -0.0873 0.9032 0.0748
-3.000 0.0260 0.01872 0.00900 -0.0877 0.8969 0.0797
-2.750 0.0610 0.01814 0.00839 -0.0891 0.8928 0.0880
-2.500 0.0886 0.01772 0.00797 -0.0891 0.8856 0.1010
-2.250 0.1202 0.01710 0.00747 -0.0898 0.8797 0.1298
-2.000 0.1541 0.01597 0.00715 -0.0915 0.8757 0.3114
-1.750 0.1768 0.01561 0.00718 -0.0905 0.8660 0.4295
-1.500 0.2104 0.01520 0.00702 -0.0912 0.8609 0.5253
-1.250 0.2323 0.01487 0.00704 -0.0896 0.8509 0.6202
-1.000 0.2615 0.01425 0.00692 -0.0887 0.8454 0.7541
-0.750 0.3071 0.01389 0.00681 -0.0914 0.8378 0.9135
-0.500 0.3590 0.01374 0.00651 -0.0963 0.8319 1.0000
-0.250 0.3845 0.01379 0.00641 -0.0957 0.8220 1.0000
0.000 0.4160 0.01375 0.00623 -0.0963 0.8146 1.0000
0.250 0.4395 0.01384 0.00623 -0.0954 0.8037 1.0000
0.500 0.4677 0.01387 0.00615 -0.0953 0.7950 1.0000
0.750 0.4950 0.01391 0.00611 -0.0950 0.7854 1.0000
1.000 0.5201 0.01400 0.00614 -0.0944 0.7751 1.0000
1.250 0.5493 0.01401 0.00608 -0.0944 0.7665 1.0000
1.500 0.5745 0.01411 0.00613 -0.0937 0.7558 1.0000
1.750 0.6003 0.01421 0.00620 -0.0932 0.7453 1.0000
2.000 0.6289 0.01425 0.00619 -0.0931 0.7362 1.0000
2.250 0.6546 0.01434 0.00627 -0.0925 0.7247 1.0000
2.500 0.6803 0.01442 0.00633 -0.0918 0.7119 1.0000
2.750 0.7065 0.01448 0.00635 -0.0912 0.6977 1.0000
3.000 0.7327 0.01453 0.00635 -0.0905 0.6819 1.0000
3.250 0.7588 0.01462 0.00641 -0.0899 0.6665 1.0000
3.500 0.7847 0.01477 0.00654 -0.0893 0.6532 1.0000
3.750 0.8109 0.01494 0.00671 -0.0888 0.6409 1.0000
4.000 0.8373 0.01513 0.00690 -0.0883 0.6287 1.0000
4.250 0.8627 0.01533 0.00710 -0.0876 0.6147 1.0000
4.500 0.8861 0.01555 0.00733 -0.0866 0.5969 1.0000
4.750 0.9086 0.01579 0.00759 -0.0854 0.5768 1.0000
5.000 0.9306 0.01602 0.00779 -0.0840 0.5541 1.0000
5.250 0.9507 0.01627 0.00804 -0.0823 0.5271 1.0000
5.500 0.9701 0.01656 0.00828 -0.0805 0.4959 1.0000
5.750 0.9887 0.01693 0.00852 -0.0787 0.4617 1.0000
6.000 1.0064 0.01738 0.00884 -0.0767 0.4257 1.0000
6.250 1.0215 0.01798 0.00924 -0.0744 0.3812 1.0000
6.500 1.0358 0.01867 0.00973 -0.0721 0.3329 1.0000
6.750 1.0490 0.01947 0.01032 -0.0698 0.2863 1.0000
7.000 1.0611 0.02038 0.01101 -0.0673 0.2459 1.0000
7.250 1.0730 0.02135 0.01180 -0.0649 0.2062 1.0000
7.500 1.0833 0.02246 0.01268 -0.0624 0.1536 1.0000
7.750 1.0891 0.02384 0.01372 -0.0594 0.1110 1.0000
8.000 1.0960 0.02511 0.01486 -0.0564 0.0916 1.0000
8.250 1.1048 0.02625 0.01598 -0.0537 0.0800 1.0000
8.500 1.1145 0.02734 0.01711 -0.0512 0.0727 1.0000
8.750 1.1237 0.02846 0.01828 -0.0488 0.0678 1.0000
9.000 1.1309 0.02973 0.01958 -0.0463 0.0648 1.0000
9.250 1.1404 0.03089 0.02087 -0.0441 0.0623 1.0000
9.500 1.1492 0.03214 0.02225 -0.0419 0.0599 1.0000
9.750 1.1577 0.03345 0.02364 -0.0399 0.0576 1.0000
10.000 1.1647 0.03493 0.02515 -0.0380 0.0554 1.0000
10.250 1.1733 0.03642 0.02671 -0.0362 0.0535 1.0000
10.500 1.1839 0.03787 0.02830 -0.0346 0.0520 1.0000
10.750 1.1947 0.03936 0.02991 -0.0331 0.0501 1.0000
11.000 1.2049 0.04091 0.03156 -0.0318 0.0481 1.0000
11.250 1.2150 0.04255 0.03324 -0.0305 0.0464 1.0000
11.500 1.2286 0.04442 0.03509 -0.0294 0.0448 1.0000
11.750 1.2408 0.04616 0.03707 -0.0282 0.0433 1.0000
12.000 1.2512 0.04805 0.03918 -0.0271 0.0415 1.0000
12.250 1.2600 0.05005 0.04134 -0.0260 0.0398 1.0000
12.500 1.2689 0.05214 0.04359 -0.0249 0.0385 1.0000
12.750 1.2773 0.05437 0.04587 -0.0241 0.0371 1.0000
13.000 1.2862 0.05718 0.04880 -0.0233 0.0356 1.0000
13.250 1.2838 0.06005 0.05200 -0.0222 0.0348 1.0000
13.500 1.2804 0.06328 0.05555 -0.0213 0.0339 1.0000
13.750 1.2748 0.06685 0.05941 -0.0207 0.0331 1.0000
14.000 1.2668 0.07068 0.06351 -0.0205 0.0324 1.0000
14.250 1.2574 0.07473 0.06780 -0.0207 0.0317 1.0000
14.500 1.2465 0.07911 0.07241 -0.0213 0.0311 1.0000
14.750 1.2335 0.08390 0.07743 -0.0225 0.0307 1.0000
15.000 1.2198 0.08902 0.08275 -0.0241 0.0302 1.0000
15.250 1.2040 0.09476 0.08871 -0.0264 0.0299 1.0000
15.500 1.1866 0.10112 0.09527 -0.0294 0.0296 1.0000
15.750 1.1644 0.10888 0.10326 -0.0336 0.0296 1.0000
16.000 1.1310 0.11980 0.11448 -0.0404 0.0301 1.0000
16.250 1.0461 0.14686 0.14190 -0.0588 0.0328 1.0000
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Polar data table (+)
Polar graphs
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