GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 50,000 Max Cl/Cd: 38.44 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe546-il-50000.txt Download as CSV file: xf-goe546-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3800 0.11905 0.11173 -0.0294 1.0000 0.2292
-9.500 -0.3570 0.11350 0.10616 -0.0279 1.0000 0.2385
-9.250 -0.3848 0.11453 0.10737 -0.0288 1.0000 0.2451
-9.000 -0.3560 0.10857 0.10136 -0.0270 1.0000 0.2569
-8.750 -0.3533 0.10562 0.09847 -0.0263 1.0000 0.2658
-8.500 -0.3729 0.10558 0.09860 -0.0258 1.0000 0.2757
-8.250 -0.3590 0.10173 0.09476 -0.0242 1.0000 0.2901
-8.000 -0.3491 0.09827 0.09134 -0.0227 1.0000 0.3023
-7.750 -0.3514 0.09589 0.08905 -0.0212 1.0000 0.3128
-7.500 -0.3796 0.09641 0.08979 -0.0186 1.0000 0.3232
-7.250 -0.3641 0.09250 0.08588 -0.0169 1.0000 0.3372
-7.000 -0.3576 0.08945 0.08288 -0.0148 1.0000 0.3492
-6.750 -0.3629 0.08745 0.08098 -0.0120 1.0000 0.3617
-6.500 -0.4052 0.08869 0.08245 -0.0065 1.0000 0.3705
-6.250 -0.4049 0.08628 0.08011 -0.0034 1.0000 0.3858
-6.000 -0.4117 0.08443 0.07836 0.0001 1.0000 0.4017
-5.750 -0.4244 0.08304 0.07707 0.0036 1.0000 0.4182
-5.250 -0.4094 0.07709 0.07119 0.0098 1.0000 0.4546
-4.250 -0.3730 0.04229 0.03411 -0.0449 1.0000 0.1647
-4.000 -0.3494 0.03898 0.03032 -0.0458 1.0000 0.1603
-3.750 -0.3258 0.03651 0.02737 -0.0462 1.0000 0.1607
-3.500 -0.3019 0.03438 0.02478 -0.0463 1.0000 0.1612
-3.250 -0.2779 0.03257 0.02255 -0.0461 1.0000 0.1613
-3.000 -0.2547 0.03116 0.02074 -0.0457 1.0000 0.1639
-2.750 -0.2319 0.03005 0.01926 -0.0451 1.0000 0.1694
-2.500 -0.2108 0.02904 0.01825 -0.0444 1.0000 0.1760
-2.250 -0.1879 0.02825 0.01720 -0.0437 1.0000 0.1827
-2.000 -0.1674 0.02753 0.01652 -0.0427 1.0000 0.1934
-1.750 -0.1456 0.02702 0.01600 -0.0420 1.0000 0.2107
-1.500 -0.1220 0.02647 0.01557 -0.0417 1.0000 0.2368
-1.250 -0.0960 0.02544 0.01532 -0.0417 1.0000 0.3409
-1.000 -0.0811 0.02287 0.01515 -0.0369 1.0000 1.0000
-0.750 -0.0594 0.02338 0.01511 -0.0370 1.0000 1.0000
-0.500 -0.0391 0.02394 0.01528 -0.0370 1.0000 1.0000
-0.250 -0.0193 0.02454 0.01556 -0.0369 1.0000 1.0000
0.000 -0.0001 0.02518 0.01591 -0.0368 1.0000 1.0000
0.250 0.0188 0.02586 0.01636 -0.0367 1.0000 1.0000
0.500 0.0561 0.02704 0.01728 -0.0400 0.9920 1.0000
0.750 0.0992 0.02833 0.01832 -0.0444 0.9798 1.0000
1.000 0.1396 0.02952 0.01932 -0.0481 0.9674 1.0000
1.250 0.1786 0.03066 0.02030 -0.0516 0.9550 1.0000
1.500 0.2173 0.03180 0.02131 -0.0548 0.9427 1.0000
1.750 0.2569 0.03294 0.02235 -0.0581 0.9307 1.0000
2.000 0.2883 0.03389 0.02323 -0.0600 0.9174 1.0000
2.250 0.3181 0.03487 0.02416 -0.0615 0.9044 1.0000
2.500 0.3491 0.03588 0.02514 -0.0632 0.8912 1.0000
2.750 0.3806 0.03692 0.02617 -0.0649 0.8780 1.0000
3.000 0.4135 0.03796 0.02721 -0.0667 0.8646 1.0000
3.250 0.4476 0.03895 0.02822 -0.0685 0.8506 1.0000
3.500 0.4819 0.03987 0.02918 -0.0702 0.8361 1.0000
3.750 0.5126 0.04068 0.03004 -0.0712 0.8197 1.0000
4.000 0.5423 0.04141 0.03083 -0.0718 0.8023 1.0000
4.250 0.5734 0.04208 0.03160 -0.0725 0.7851 1.0000
4.500 0.6050 0.04272 0.03234 -0.0731 0.7682 1.0000
4.750 0.6363 0.04335 0.03308 -0.0736 0.7519 1.0000
5.000 0.6680 0.04392 0.03380 -0.0741 0.7357 1.0000
5.250 0.7010 0.04436 0.03439 -0.0745 0.7193 1.0000
5.500 0.7355 0.04468 0.03488 -0.0748 0.7030 1.0000
5.750 0.7744 0.04464 0.03507 -0.0753 0.6865 1.0000
6.000 0.8173 0.04420 0.03489 -0.0758 0.6703 1.0000
6.250 0.8408 0.04470 0.03557 -0.0745 0.6509 1.0000
6.500 0.8717 0.04460 0.03573 -0.0735 0.6312 1.0000
6.750 1.0212 0.03269 0.02438 -0.0756 0.5900 1.0000
7.000 1.0628 0.02954 0.02125 -0.0725 0.5455 1.0000
7.250 1.0762 0.02888 0.02067 -0.0681 0.5046 1.0000
7.500 1.0886 0.02832 0.02007 -0.0635 0.4570 1.0000
7.750 1.0888 0.02850 0.01996 -0.0574 0.3895 1.0000
8.000 1.0741 0.03008 0.02074 -0.0502 0.2964 1.0000
8.250 1.0651 0.03290 0.02254 -0.0448 0.2263 1.0000
8.500 1.0788 0.03535 0.02460 -0.0427 0.1864 1.0000
8.750 1.1125 0.03766 0.02678 -0.0431 0.1633 1.0000
9.000 1.1504 0.04004 0.02912 -0.0440 0.1493 1.0000
9.250 1.1845 0.04255 0.03160 -0.0448 0.1387 1.0000
9.500 1.2131 0.04538 0.03475 -0.0447 0.1328 1.0000
9.750 1.2460 0.04880 0.03815 -0.0456 0.1272 1.0000
10.000 1.2532 0.05166 0.04160 -0.0429 0.1241 1.0000
10.250 1.2605 0.05491 0.04530 -0.0406 0.1215 1.0000
10.500 1.2645 0.05858 0.04940 -0.0382 0.1205 1.0000
10.750 1.2619 0.06232 0.05353 -0.0355 0.1199 1.0000
11.000 1.2532 0.06607 0.05765 -0.0324 0.1194 1.0000
11.250 1.2365 0.06984 0.06175 -0.0289 0.1194 1.0000
11.500 1.2120 0.07378 0.06597 -0.0255 0.1201 1.0000
11.750 1.1825 0.07834 0.07079 -0.0231 0.1213 1.0000
12.000 1.1504 0.08373 0.07639 -0.0223 0.1229 1.0000
12.250 1.1184 0.09001 0.08282 -0.0229 0.1246 1.0000
12.500 1.0924 0.09686 0.08977 -0.0248 0.1261 1.0000
12.750 1.0734 0.10401 0.09698 -0.0270 0.1272 1.0000
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