GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 546 AIRFOIL (goe546-il) Reynolds number: 50,000 Max Cl/Cd: 38.61 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe546-il-50000-n5.txt Download as CSV file: xf-goe546-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4048 0.09656 0.08948 -0.0458 1.0000 0.0700
-8.750 -0.4099 0.09334 0.08636 -0.0456 1.0000 0.0698
-8.500 -0.4191 0.09031 0.08344 -0.0451 1.0000 0.0697
-8.250 -0.4283 0.08741 0.08065 -0.0443 1.0000 0.0695
-8.000 -0.4369 0.08403 0.07736 -0.0444 1.0000 0.0692
-7.750 -0.4457 0.08048 0.07387 -0.0447 1.0000 0.0690
-7.500 -0.4541 0.07672 0.07015 -0.0451 1.0000 0.0687
-7.250 -0.4613 0.07290 0.06633 -0.0454 1.0000 0.0683
-7.000 -0.4666 0.06898 0.06238 -0.0458 1.0000 0.0678
-6.750 -0.4699 0.06480 0.05810 -0.0465 1.0000 0.0673
-6.500 -0.4701 0.06043 0.05354 -0.0474 1.0000 0.0669
-6.250 -0.4669 0.05590 0.04870 -0.0487 1.0000 0.0674
-6.000 -0.4594 0.05137 0.04369 -0.0501 1.0000 0.0686
-5.750 -0.4471 0.04741 0.03911 -0.0511 1.0000 0.0699
-5.500 -0.4323 0.04411 0.03543 -0.0512 1.0000 0.0707
-5.250 -0.4138 0.04128 0.03229 -0.0514 0.9994 0.0716
-5.000 -0.3822 0.03910 0.02992 -0.0538 0.9942 0.0747
-4.750 -0.3496 0.03686 0.02721 -0.0561 0.9886 0.0784
-4.500 -0.3156 0.03460 0.02439 -0.0581 0.9833 0.0804
-4.250 -0.2818 0.03277 0.02204 -0.0597 0.9777 0.0825
-4.000 -0.2491 0.03131 0.02030 -0.0612 0.9721 0.0865
-3.750 -0.2159 0.03018 0.01901 -0.0627 0.9661 0.0911
-3.500 -0.1834 0.02914 0.01773 -0.0637 0.9600 0.0944
-3.250 -0.1499 0.02827 0.01660 -0.0647 0.9538 0.0983
-3.000 -0.1177 0.02745 0.01579 -0.0659 0.9474 0.1053
-2.750 -0.0850 0.02688 0.01503 -0.0670 0.9404 0.1145
-2.500 -0.0514 0.02622 0.01434 -0.0683 0.9340 0.1248
-2.250 -0.0189 0.02563 0.01372 -0.0696 0.9265 0.1443
-2.000 0.0188 0.02461 0.01320 -0.0721 0.9212 0.2091
-1.750 0.0446 0.02369 0.01330 -0.0722 0.9128 0.4334
-1.500 0.0772 0.02324 0.01330 -0.0726 0.9068 0.5845
-1.250 0.0946 0.02261 0.01343 -0.0693 0.8976 0.7538
-1.000 0.1539 0.02227 0.01308 -0.0749 0.8927 1.0000
-0.750 0.1833 0.02247 0.01298 -0.0756 0.8826 1.0000
-0.500 0.2245 0.02258 0.01279 -0.0783 0.8762 1.0000
0.000 0.2858 0.02295 0.01274 -0.0797 0.8573 1.0000
0.250 0.3171 0.02313 0.01275 -0.0805 0.8481 1.0000
0.500 0.3455 0.02336 0.01284 -0.0808 0.8383 1.0000
0.750 0.3818 0.02347 0.01283 -0.0823 0.8310 1.0000
1.000 0.4061 0.02376 0.01303 -0.0818 0.8200 1.0000
1.250 0.4446 0.02379 0.01297 -0.0835 0.8139 1.0000
1.750 0.4925 0.02440 0.01348 -0.0823 0.7921 1.0000
2.000 0.5265 0.02447 0.01353 -0.0832 0.7845 1.0000
2.250 0.5491 0.02481 0.01386 -0.0823 0.7731 1.0000
2.500 0.5783 0.02499 0.01404 -0.0824 0.7640 1.0000
2.750 0.6082 0.02512 0.01418 -0.0826 0.7547 1.0000
3.000 0.6315 0.02544 0.01455 -0.0818 0.7433 1.0000
3.250 0.6610 0.02556 0.01471 -0.0818 0.7337 1.0000
3.500 0.6916 0.02560 0.01481 -0.0818 0.7239 1.0000
3.750 0.7169 0.02573 0.01500 -0.0810 0.7108 1.0000
4.000 0.7447 0.02568 0.01502 -0.0803 0.6971 1.0000
4.250 0.7731 0.02559 0.01500 -0.0797 0.6830 1.0000
4.500 0.8015 0.02555 0.01506 -0.0791 0.6694 1.0000
4.750 0.8303 0.02557 0.01517 -0.0786 0.6564 1.0000
5.000 0.8602 0.02557 0.01528 -0.0783 0.6437 1.0000
5.250 0.8903 0.02561 0.01545 -0.0781 0.6308 1.0000
5.500 0.9155 0.02583 0.01580 -0.0772 0.6159 1.0000
5.750 0.9406 0.02608 0.01619 -0.0763 0.6005 1.0000
6.000 0.9656 0.02633 0.01660 -0.0753 0.5845 1.0000
6.250 0.9866 0.02662 0.01703 -0.0737 0.5650 1.0000
6.500 1.0070 0.02653 0.01699 -0.0714 0.5373 1.0000
6.750 1.0186 0.02665 0.01711 -0.0679 0.5018 1.0000
7.000 1.0317 0.02672 0.01706 -0.0646 0.4607 1.0000
7.250 1.0416 0.02718 0.01741 -0.0613 0.4188 1.0000
7.500 1.0512 0.02785 0.01798 -0.0582 0.3780 1.0000
7.750 1.0579 0.02872 0.01870 -0.0550 0.3346 1.0000
8.000 1.0629 0.02979 0.01960 -0.0517 0.2917 1.0000
8.250 1.0645 0.03124 0.02080 -0.0483 0.2477 1.0000
8.500 1.0646 0.03300 0.02232 -0.0453 0.2044 1.0000
8.750 1.0646 0.03499 0.02409 -0.0426 0.1622 1.0000
9.000 1.0642 0.03717 0.02604 -0.0401 0.1354 1.0000
9.250 1.0654 0.03937 0.02811 -0.0379 0.1206 1.0000
9.500 1.0689 0.04151 0.03021 -0.0360 0.1104 1.0000
9.750 1.0731 0.04367 0.03229 -0.0342 0.1036 1.0000
10.000 1.0828 0.04551 0.03427 -0.0327 0.0969 1.0000
10.250 1.0913 0.04748 0.03624 -0.0313 0.0915 1.0000
10.500 1.1061 0.04914 0.03810 -0.0301 0.0860 1.0000
10.750 1.1243 0.05074 0.03985 -0.0290 0.0817 1.0000
11.000 1.1489 0.05230 0.04139 -0.0281 0.0779 1.0000
11.250 1.1690 0.05422 0.04360 -0.0273 0.0743 1.0000
11.500 1.1826 0.05639 0.04608 -0.0263 0.0706 1.0000
11.750 1.1987 0.05863 0.04848 -0.0255 0.0679 1.0000
12.000 1.2202 0.06107 0.05092 -0.0251 0.0651 1.0000
12.250 1.2184 0.06419 0.05449 -0.0237 0.0634 1.0000
12.500 1.2150 0.06757 0.05824 -0.0227 0.0617 1.0000
12.750 1.2100 0.07120 0.06219 -0.0219 0.0603 1.0000
13.000 1.2032 0.07517 0.06644 -0.0214 0.0593 1.0000
13.250 1.1933 0.07947 0.07101 -0.0214 0.0585 1.0000
13.500 1.1802 0.08419 0.07597 -0.0219 0.0578 1.0000
13.750 1.1642 0.08946 0.08149 -0.0231 0.0573 1.0000
14.000 1.1432 0.09569 0.08795 -0.0253 0.0571 1.0000
14.250 1.1107 0.10427 0.09682 -0.0296 0.0577 1.0000
14.500 1.0629 0.11709 0.10990 -0.0376 0.0595 1.0000
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Polar data table (+)
Polar graphs
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