GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 500,000 Max Cl/Cd: 74.06 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe575-il-500000.txt Download as CSV file: xf-goe575-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 575 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6249 0.07632 0.07407 -0.0391 1.0000 0.0455
-9.500 -0.6304 0.07464 0.07237 -0.0379 0.9998 0.0458
-9.250 -0.9353 0.03557 0.03044 -0.0125 0.9788 0.0392
-9.000 -0.9125 0.03348 0.02826 -0.0125 0.9732 0.0398
-8.750 -0.8878 0.03273 0.02752 -0.0122 0.9694 0.0405
-8.500 -0.8586 0.03200 0.02673 -0.0128 0.9671 0.0411
-8.250 -0.8436 0.03107 0.02570 -0.0104 0.9613 0.0419
-8.000 -0.8203 0.03030 0.02477 -0.0096 0.9582 0.0429
-7.750 -0.7931 0.02934 0.02356 -0.0095 0.9563 0.0437
-7.500 -0.7835 0.02857 0.02259 -0.0055 0.9496 0.0443
-7.250 -0.7587 0.02759 0.02136 -0.0049 0.9469 0.0450
-7.000 -0.7275 0.02591 0.01960 -0.0059 0.9457 0.0458
-6.750 -0.7107 0.02506 0.01872 -0.0036 0.9398 0.0465
-6.500 -0.6814 0.02427 0.01788 -0.0038 0.9372 0.0471
-6.250 -0.6478 0.02354 0.01708 -0.0050 0.9354 0.0481
-6.000 -0.6124 0.02289 0.01634 -0.0064 0.9341 0.0492
-5.750 -0.5936 0.02220 0.01557 -0.0042 0.9279 0.0497
-5.500 -0.5628 0.02174 0.01500 -0.0046 0.9250 0.0506
-5.250 -0.5275 0.02124 0.01440 -0.0058 0.9232 0.0511
-5.000 -0.4857 0.01995 0.01307 -0.0088 0.9224 0.0520
-4.750 -0.4448 0.01907 0.01224 -0.0116 0.9215 0.0536
-4.500 -0.4220 0.01839 0.01155 -0.0102 0.9142 0.0543
-4.250 -0.3849 0.01780 0.01096 -0.0120 0.9116 0.0554
-4.000 -0.3416 0.01706 0.01020 -0.0149 0.9096 0.0565
-3.750 -0.2994 0.01644 0.00956 -0.0177 0.9083 0.0578
-3.500 -0.2770 0.01599 0.00909 -0.0162 0.9007 0.0582
-3.250 -0.2404 0.01530 0.00842 -0.0179 0.8978 0.0596
-3.000 -0.1984 0.01455 0.00771 -0.0207 0.8957 0.0620
-2.750 -0.1568 0.01397 0.00715 -0.0235 0.8941 0.0635
-2.500 -0.1311 0.01358 0.00676 -0.0227 0.8866 0.0646
-2.250 -0.0979 0.01311 0.00628 -0.0235 0.8815 0.0664
-2.000 -0.0574 0.01251 0.00573 -0.0259 0.8780 0.0702
-1.750 -0.0341 0.01218 0.00544 -0.0246 0.8656 0.0749
-1.500 0.0018 0.01169 0.00509 -0.0261 0.8561 0.0952
-1.250 0.0435 0.01118 0.00472 -0.0288 0.8452 0.1287
-1.000 0.0906 0.01072 0.00430 -0.0327 0.8261 0.1516
-0.750 0.1458 0.01031 0.00387 -0.0385 0.8008 0.1696
-0.500 0.2059 0.01004 0.00347 -0.0455 0.7640 0.1879
-0.250 0.2425 0.01004 0.00334 -0.0473 0.7311 0.2011
0.000 0.2700 0.01011 0.00330 -0.0472 0.7056 0.2131
0.250 0.2933 0.01015 0.00330 -0.0461 0.6828 0.2321
0.500 0.3157 0.01015 0.00332 -0.0449 0.6626 0.2597
0.750 0.3404 0.00981 0.00339 -0.0445 0.6397 0.4034
1.000 0.5390 0.01140 0.00638 -0.0822 0.5872 0.9721
1.250 0.6066 0.01192 0.00669 -0.0908 0.5551 0.9841
1.500 0.7099 0.01149 0.00601 -0.1076 0.5160 1.0000
1.750 0.7288 0.01162 0.00603 -0.1057 0.4952 1.0000
2.000 0.7478 0.01177 0.00606 -0.1038 0.4759 1.0000
2.250 0.7672 0.01192 0.00611 -0.1020 0.4575 1.0000
2.500 0.7867 0.01208 0.00617 -0.1003 0.4404 1.0000
2.750 0.8066 0.01224 0.00624 -0.0986 0.4258 1.0000
3.000 0.8264 0.01241 0.00632 -0.0969 0.4126 1.0000
3.250 0.8467 0.01255 0.00640 -0.0953 0.3990 1.0000
3.500 0.8675 0.01269 0.00650 -0.0939 0.3894 1.0000
3.750 0.8870 0.01289 0.00661 -0.0921 0.3771 1.0000
4.000 0.9076 0.01303 0.00672 -0.0906 0.3661 1.0000
4.250 0.9277 0.01320 0.00684 -0.0890 0.3567 1.0000
4.500 0.9482 0.01335 0.00697 -0.0875 0.3486 1.0000
4.750 0.9677 0.01354 0.00711 -0.0858 0.3384 1.0000
5.000 0.9875 0.01372 0.00725 -0.0842 0.3295 1.0000
5.250 1.0069 0.01390 0.00741 -0.0825 0.3208 1.0000
5.500 1.0264 0.01409 0.00757 -0.0808 0.3120 1.0000
5.750 1.0457 0.01429 0.00775 -0.0790 0.3031 1.0000
6.000 1.0647 0.01449 0.00792 -0.0773 0.2936 1.0000
6.250 1.0840 0.01468 0.00811 -0.0756 0.2854 1.0000
6.500 1.1019 0.01494 0.00831 -0.0737 0.2739 1.0000
6.750 1.1213 0.01514 0.00851 -0.0720 0.2638 1.0000
7.000 1.1391 0.01541 0.00874 -0.0701 0.2523 1.0000
7.250 1.1560 0.01572 0.00898 -0.0680 0.2397 1.0000
7.500 1.1740 0.01598 0.00923 -0.0661 0.2287 1.0000
7.750 1.1905 0.01630 0.00952 -0.0640 0.2180 1.0000
8.000 1.2058 0.01668 0.00984 -0.0617 0.2073 1.0000
8.250 1.2227 0.01699 0.01015 -0.0596 0.1993 1.0000
8.500 1.2376 0.01739 0.01051 -0.0573 0.1920 1.0000
8.750 1.2546 0.01769 0.01084 -0.0553 0.1856 1.0000
9.000 1.2688 0.01813 0.01124 -0.0529 0.1788 1.0000
9.250 1.2844 0.01848 0.01162 -0.0507 0.1734 1.0000
9.500 1.2994 0.01886 0.01202 -0.0485 0.1686 1.0000
9.750 1.3118 0.01937 0.01250 -0.0458 0.1622 1.0000
10.000 1.3282 0.01970 0.01289 -0.0439 0.1575 1.0000
10.250 1.3420 0.02014 0.01334 -0.0415 0.1516 1.0000
10.500 1.3549 0.02063 0.01384 -0.0390 0.1448 1.0000
10.750 1.3686 0.02109 0.01432 -0.0368 0.1378 1.0000
11.000 1.3807 0.02165 0.01487 -0.0342 0.1265 1.0000
11.250 1.3904 0.02232 0.01551 -0.0314 0.1152 1.0000
11.500 1.3971 0.02319 0.01627 -0.0283 0.1002 1.0000
11.750 1.4042 0.02402 0.01709 -0.0252 0.0938 1.0000
12.000 1.4098 0.02496 0.01800 -0.0220 0.0869 1.0000
12.250 1.4157 0.02589 0.01897 -0.0189 0.0837 1.0000
12.500 1.4239 0.02672 0.01985 -0.0162 0.0818 1.0000
12.750 1.4288 0.02777 0.02093 -0.0133 0.0792 1.0000
13.000 1.4308 0.02902 0.02220 -0.0101 0.0763 1.0000
13.250 1.4332 0.03030 0.02353 -0.0072 0.0744 1.0000
13.500 1.4395 0.03137 0.02469 -0.0048 0.0734 1.0000
13.750 1.4449 0.03256 0.02596 -0.0025 0.0724 1.0000
14.000 1.4482 0.03394 0.02742 -0.0002 0.0709 1.0000
14.250 1.4499 0.03552 0.02907 0.0021 0.0698 1.0000
14.500 1.4517 0.03718 0.03080 0.0042 0.0692 1.0000
14.750 1.4494 0.03925 0.03291 0.0062 0.0675 1.0000
15.000 1.4464 0.04152 0.03526 0.0081 0.0667 1.0000
15.250 1.4433 0.04391 0.03773 0.0096 0.0654 1.0000
15.500 1.4418 0.04628 0.04020 0.0109 0.0653 1.0000
15.750 1.4449 0.04824 0.04227 0.0118 0.0647 1.0000
16.000 1.4460 0.05050 0.04463 0.0125 0.0638 1.0000
16.250 1.4452 0.05300 0.04723 0.0132 0.0633 1.0000
16.500 1.4443 0.05559 0.04991 0.0137 0.0624 1.0000
16.750 1.4421 0.05836 0.05278 0.0141 0.0621 1.0000
17.000 1.4382 0.06141 0.05592 0.0143 0.0607 1.0000
17.250 1.4334 0.06461 0.05919 0.0144 0.0601 1.0000
17.500 1.4278 0.06797 0.06262 0.0143 0.0593 1.0000
17.750 1.4208 0.07153 0.06624 0.0141 0.0584 1.0000
18.000 1.4129 0.07513 0.06990 0.0140 0.0576 1.0000
18.250 1.4095 0.07836 0.07322 0.0136 0.0570 1.0000
18.500 1.4063 0.08174 0.07672 0.0130 0.0564 1.0000
18.750 1.4022 0.08529 0.08040 0.0121 0.0555 1.0000
19.000 1.3974 0.08895 0.08416 0.0113 0.0547 1.0000
19.250 1.3924 0.09258 0.08788 0.0105 0.0540 1.0000
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