GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe564-il-1000000-n5.txt Download as CSV file: xf-goe564-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0313 0.03237 0.02963 -0.0664 1.0000 0.0047
-12.500 -1.0185 0.02841 0.02538 -0.0680 0.9985 0.0048
-12.250 -0.9993 0.02589 0.02265 -0.0691 0.9969 0.0049
-12.000 -0.9769 0.02410 0.02068 -0.0699 0.9955 0.0051
-11.750 -0.9535 0.02257 0.01898 -0.0706 0.9943 0.0053
-11.500 -0.9311 0.02129 0.01754 -0.0707 0.9926 0.0055
-11.250 -0.9069 0.02017 0.01627 -0.0710 0.9908 0.0058
-11.000 -0.8813 0.01910 0.01506 -0.0715 0.9893 0.0059
-10.750 -0.8543 0.01820 0.01402 -0.0721 0.9879 0.0061
-10.500 -0.8272 0.01713 0.01280 -0.0727 0.9868 0.0064
-10.250 -0.7993 0.01619 0.01174 -0.0735 0.9859 0.0069
-10.000 -0.7754 0.01548 0.01094 -0.0731 0.9834 0.0072
-9.750 -0.7494 0.01483 0.01019 -0.0732 0.9813 0.0076
-9.500 -0.7216 0.01423 0.00949 -0.0735 0.9796 0.0080
-9.250 -0.6925 0.01369 0.00886 -0.0741 0.9782 0.0085
-9.000 -0.6625 0.01309 0.00818 -0.0749 0.9770 0.0092
-8.750 -0.6314 0.01254 0.00758 -0.0758 0.9759 0.0101
-8.500 -0.6058 0.01210 0.00710 -0.0755 0.9724 0.0112
-8.250 -0.5777 0.01169 0.00662 -0.0757 0.9695 0.0121
-8.000 -0.5476 0.01131 0.00623 -0.0764 0.9675 0.0139
-7.750 -0.5165 0.01100 0.00590 -0.0772 0.9659 0.0155
-7.500 -0.4849 0.01068 0.00555 -0.0781 0.9644 0.0168
-7.250 -0.4584 0.01045 0.00533 -0.0779 0.9602 0.0184
-7.000 -0.4298 0.01028 0.00516 -0.0781 0.9565 0.0201
-6.750 -0.3988 0.01008 0.00492 -0.0788 0.9537 0.0214
-6.500 -0.3668 0.00989 0.00469 -0.0797 0.9512 0.0222
-6.250 -0.3393 0.00976 0.00453 -0.0796 0.9458 0.0226
-6.000 -0.3104 0.00938 0.00410 -0.0799 0.9406 0.0238
-5.750 -0.2799 0.00905 0.00372 -0.0805 0.9365 0.0251
-5.500 -0.2528 0.00883 0.00348 -0.0804 0.9300 0.0263
-5.250 -0.2236 0.00862 0.00324 -0.0806 0.9239 0.0273
-5.000 -0.1953 0.00843 0.00301 -0.0807 0.9176 0.0281
-4.750 -0.1671 0.00825 0.00277 -0.0807 0.9097 0.0289
-4.500 -0.1394 0.00807 0.00254 -0.0806 0.9017 0.0294
-4.250 -0.1118 0.00791 0.00232 -0.0805 0.8934 0.0299
-4.000 -0.0847 0.00776 0.00212 -0.0802 0.8855 0.0303
-3.500 -0.0305 0.00752 0.00179 -0.0797 0.8709 0.0312
-3.000 0.0231 0.00725 0.00146 -0.0791 0.8562 0.0361
-2.750 0.0496 0.00715 0.00134 -0.0787 0.8467 0.0390
-2.500 0.0756 0.00707 0.00123 -0.0782 0.8339 0.0463
-2.250 0.1008 0.00694 0.00113 -0.0775 0.8183 0.0668
-2.000 0.1263 0.00689 0.00107 -0.0769 0.8013 0.0798
-1.750 0.1521 0.00686 0.00102 -0.0763 0.7854 0.0891
-1.500 0.1780 0.00683 0.00096 -0.0758 0.7685 0.0967
-1.250 0.2024 0.00687 0.00091 -0.0749 0.7370 0.1026
-1.000 0.2238 0.00707 0.00088 -0.0734 0.6766 0.1065
-0.750 0.2462 0.00724 0.00088 -0.0722 0.6319 0.1131
-0.500 0.2709 0.00735 0.00089 -0.0715 0.6051 0.1193
-0.250 0.2957 0.00743 0.00090 -0.0708 0.5787 0.1282
0.000 0.3203 0.00749 0.00092 -0.0701 0.5481 0.1483
0.250 0.3442 0.00753 0.00094 -0.0693 0.5112 0.1856
0.500 0.3674 0.00758 0.00098 -0.0684 0.4677 0.2387
0.750 0.3901 0.00761 0.00105 -0.0675 0.4252 0.3137
1.000 0.4125 0.00762 0.00113 -0.0665 0.3841 0.4044
1.250 0.4344 0.00759 0.00122 -0.0654 0.3445 0.5059
1.500 0.4558 0.00758 0.00134 -0.0642 0.3026 0.6092
1.750 0.4753 0.00747 0.00146 -0.0625 0.2673 0.7366
2.000 0.5250 0.00726 0.00172 -0.0673 0.2320 0.9728
2.250 0.5717 0.00750 0.00185 -0.0716 0.2125 0.9917
2.500 0.6093 0.00768 0.00196 -0.0739 0.1997 0.9987
3.000 0.6610 0.00803 0.00217 -0.0731 0.1729 1.0000
3.250 0.6846 0.00816 0.00227 -0.0722 0.1671 1.0000
3.500 0.7079 0.00832 0.00239 -0.0712 0.1584 1.0000
3.750 0.7315 0.00846 0.00251 -0.0703 0.1522 1.0000
4.000 0.7549 0.00862 0.00264 -0.0693 0.1434 1.0000
4.250 0.7784 0.00879 0.00278 -0.0684 0.1341 1.0000
4.500 0.8010 0.00903 0.00294 -0.0674 0.1171 1.0000
4.750 0.8224 0.00936 0.00315 -0.0661 0.0954 1.0000
5.000 0.8449 0.00962 0.00336 -0.0650 0.0858 1.0000
5.250 0.8674 0.00988 0.00359 -0.0640 0.0787 1.0000
5.500 0.8910 0.01006 0.00378 -0.0631 0.0755 1.0000
5.750 0.9146 0.01025 0.00398 -0.0622 0.0713 1.0000
6.000 0.9372 0.01053 0.00422 -0.0612 0.0641 1.0000
6.250 0.9575 0.01099 0.00454 -0.0598 0.0395 1.0000
6.500 0.9793 0.01134 0.00486 -0.0587 0.0312 1.0000
6.750 1.0015 0.01167 0.00518 -0.0576 0.0271 1.0000
7.000 1.0242 0.01196 0.00547 -0.0567 0.0239 1.0000
7.250 1.0467 0.01226 0.00578 -0.0557 0.0206 1.0000
7.500 1.0684 0.01263 0.00615 -0.0546 0.0169 1.0000
7.750 1.0903 0.01298 0.00650 -0.0535 0.0146 1.0000
8.000 1.1116 0.01339 0.00690 -0.0524 0.0122 1.0000
8.250 1.1336 0.01372 0.00726 -0.0514 0.0111 1.0000
8.500 1.1548 0.01411 0.00767 -0.0502 0.0100 1.0000
8.750 1.1754 0.01456 0.00815 -0.0490 0.0089 1.0000
9.000 1.1962 0.01498 0.00860 -0.0478 0.0084 1.0000
9.250 1.2169 0.01538 0.00904 -0.0466 0.0079 1.0000
9.500 1.2372 0.01580 0.00951 -0.0454 0.0074 1.0000
9.750 1.2566 0.01629 0.01002 -0.0441 0.0069 1.0000
10.000 1.2753 0.01682 0.01059 -0.0426 0.0065 1.0000
10.250 1.2933 0.01736 0.01118 -0.0410 0.0060 1.0000
10.500 1.3116 0.01786 0.01175 -0.0395 0.0058 1.0000
10.750 1.3283 0.01840 0.01235 -0.0378 0.0056 1.0000
11.000 1.3436 0.01892 0.01293 -0.0357 0.0053 1.0000
11.250 1.3582 0.01947 0.01354 -0.0336 0.0051 1.0000
11.500 1.3718 0.02009 0.01420 -0.0314 0.0049 1.0000
11.750 1.3852 0.02071 0.01489 -0.0292 0.0047 1.0000
12.000 1.3968 0.02147 0.01570 -0.0269 0.0045 1.0000
12.250 1.4058 0.02239 0.01672 -0.0242 0.0043 1.0000
12.500 1.4159 0.02325 0.01767 -0.0219 0.0042 1.0000
12.750 1.4262 0.02410 0.01860 -0.0196 0.0041 1.0000
13.000 1.4350 0.02505 0.01964 -0.0173 0.0041 1.0000
13.250 1.4428 0.02609 0.02078 -0.0151 0.0040 1.0000
13.500 1.4514 0.02710 0.02188 -0.0130 0.0038 1.0000
13.750 1.4572 0.02834 0.02322 -0.0109 0.0038 1.0000
14.000 1.4634 0.02959 0.02456 -0.0089 0.0037 1.0000
14.250 1.4698 0.03088 0.02593 -0.0072 0.0036 1.0000
14.500 1.4734 0.03245 0.02760 -0.0055 0.0035 1.0000
14.750 1.4748 0.03429 0.02955 -0.0038 0.0034 1.0000
15.000 1.4787 0.03600 0.03134 -0.0026 0.0033 1.0000
15.250 1.4745 0.03857 0.03406 -0.0013 0.0033 1.0000
15.500 1.4742 0.04091 0.03650 -0.0005 0.0032 1.0000
15.750 1.4735 0.04344 0.03913 -0.0001 0.0032 1.0000
16.000 1.4684 0.04667 0.04247 0.0000 0.0031 1.0000
16.250 1.4607 0.05044 0.04638 -0.0005 0.0031 1.0000
16.500 1.4497 0.05498 0.05105 -0.0016 0.0030 1.0000
16.750 1.4357 0.06028 0.05649 -0.0035 0.0029 1.0000
17.000 1.4228 0.06571 0.06206 -0.0057 0.0030 1.0000
17.250 1.4005 0.07314 0.06967 -0.0092 0.0030 1.0000
17.500 1.3781 0.08109 0.07777 -0.0132 0.0030 1.0000
17.750 1.3544 0.08965 0.08649 -0.0177 0.0030 1.0000
18.000 1.3230 0.10003 0.09704 -0.0232 0.0031 1.0000
18.250 1.2862 0.11167 0.10885 -0.0293 0.0031 1.0000
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Polar data table (+)
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