GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.59 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe529-il-1000000.txt Download as CSV file: xf-goe529-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2741 0.11548 0.11386 -0.0352 1.0000 0.0138
-10.500 -0.2730 0.11211 0.11050 -0.0364 1.0000 0.0139
-10.250 -0.2708 0.10900 0.10741 -0.0370 1.0000 0.0139
-10.000 -0.2692 0.10590 0.10433 -0.0375 1.0000 0.0139
-9.750 -0.2677 0.10213 0.10059 -0.0376 0.9999 0.0141
-9.500 -0.2480 0.09926 0.09771 -0.0407 0.9983 0.0144
-9.250 -0.2332 0.09632 0.09477 -0.0434 0.9895 0.0148
-9.000 -0.2170 0.09302 0.09147 -0.0470 0.9803 0.0154
-8.750 -0.1954 0.08878 0.08721 -0.0528 0.9688 0.0164
-8.500 -0.1683 0.08135 0.07974 -0.0657 0.9564 0.0175
-8.250 -0.1291 0.07429 0.07261 -0.0788 0.9368 0.0175
-8.000 -0.1071 0.06915 0.06728 -0.0863 0.8934 0.0181
-7.750 -0.0970 0.06829 0.06622 -0.0856 0.8494 0.0185
-7.500 -0.1032 0.06546 0.06328 -0.0859 0.8180 0.0184
-7.250 -0.0950 0.06387 0.06158 -0.0863 0.7921 0.0189
-7.000 -0.0866 0.06172 0.05933 -0.0877 0.7682 0.0203
-6.250 -0.1054 0.01888 0.01480 -0.1109 0.7189 0.0217
-6.000 -0.0881 0.01582 0.01120 -0.1102 0.7025 0.0228
-5.750 -0.0626 0.01560 0.01089 -0.1099 0.6884 0.0233
-5.500 -0.0361 0.01564 0.01089 -0.1097 0.6773 0.0240
-5.250 -0.0104 0.01528 0.01040 -0.1093 0.6684 0.0248
-5.000 0.0150 0.01449 0.00942 -0.1090 0.6607 0.0257
-4.750 0.0405 0.01379 0.00851 -0.1086 0.6540 0.0264
-4.500 0.0676 0.01350 0.00811 -0.1083 0.6486 0.0270
-4.250 0.0933 0.01265 0.00703 -0.1080 0.6433 0.0278
-4.000 0.1181 0.01144 0.00563 -0.1075 0.6385 0.0287
-3.750 0.1450 0.01097 0.00510 -0.1073 0.6340 0.0294
-3.500 0.1720 0.01065 0.00472 -0.1071 0.6295 0.0301
-3.250 0.1989 0.01042 0.00442 -0.1068 0.6253 0.0310
-3.000 0.2262 0.01009 0.00402 -0.1066 0.6215 0.0316
-2.750 0.2534 0.00976 0.00364 -0.1064 0.6175 0.0322
-2.500 0.2805 0.00947 0.00329 -0.1061 0.6133 0.0327
-2.250 0.3075 0.00926 0.00301 -0.1058 0.6092 0.0333
-2.000 0.3350 0.00906 0.00278 -0.1057 0.6058 0.0338
-1.750 0.3626 0.00890 0.00260 -0.1055 0.6019 0.0344
-1.500 0.3891 0.00853 0.00215 -0.1051 0.5977 0.0359
-1.250 0.4161 0.00839 0.00197 -0.1049 0.5934 0.0373
-1.000 0.4438 0.00825 0.00184 -0.1047 0.5898 0.0386
-0.750 0.4714 0.00814 0.00172 -0.1046 0.5854 0.0401
-0.500 0.4988 0.00808 0.00162 -0.1044 0.5807 0.0419
-0.250 0.5261 0.00800 0.00153 -0.1042 0.5758 0.0459
0.000 0.5535 0.00787 0.00147 -0.1040 0.5688 0.0645
0.250 0.5804 0.00781 0.00145 -0.1037 0.5613 0.0906
0.500 0.6079 0.00775 0.00143 -0.1036 0.5528 0.1074
0.750 0.6349 0.00772 0.00143 -0.1034 0.5459 0.1297
1.000 0.6623 0.00767 0.00144 -0.1033 0.5383 0.1582
1.250 0.6891 0.00763 0.00146 -0.1031 0.5299 0.1938
1.500 0.7154 0.00746 0.00151 -0.1028 0.5205 0.2919
1.750 0.7632 0.00607 0.00170 -0.1077 0.5091 1.0000
2.000 0.7886 0.00617 0.00173 -0.1072 0.4977 1.0000
2.250 0.8139 0.00629 0.00177 -0.1066 0.4859 1.0000
2.500 0.8390 0.00643 0.00183 -0.1060 0.4739 1.0000
2.750 0.8645 0.00656 0.00189 -0.1055 0.4627 1.0000
3.000 0.8899 0.00669 0.00197 -0.1050 0.4525 1.0000
3.250 0.9151 0.00685 0.00207 -0.1045 0.4430 1.0000
3.500 0.9406 0.00699 0.00217 -0.1040 0.4339 1.0000
3.750 0.9661 0.00713 0.00227 -0.1036 0.4259 1.0000
4.000 0.9915 0.00728 0.00238 -0.1031 0.4180 1.0000
4.250 1.0171 0.00742 0.00250 -0.1027 0.4110 1.0000
4.500 1.0426 0.00757 0.00263 -0.1023 0.4037 1.0000
4.750 1.0681 0.00773 0.00276 -0.1019 0.3961 1.0000
5.000 1.0932 0.00790 0.00290 -0.1014 0.3874 1.0000
5.250 1.1184 0.00807 0.00304 -0.1009 0.3765 1.0000
5.500 1.1426 0.00830 0.00320 -0.1004 0.3609 1.0000
5.750 1.1672 0.00851 0.00336 -0.0998 0.3485 1.0000
6.000 1.1915 0.00873 0.00355 -0.0993 0.3360 1.0000
6.250 1.2154 0.00898 0.00374 -0.0987 0.3217 1.0000
6.500 1.2391 0.00924 0.00395 -0.0980 0.3077 1.0000
6.750 1.2614 0.00958 0.00421 -0.0972 0.2875 1.0000
7.000 1.2825 0.01001 0.00452 -0.0961 0.2647 1.0000
7.250 1.3029 0.01047 0.00486 -0.0950 0.2419 1.0000
7.500 1.3228 0.01095 0.00523 -0.0938 0.2194 1.0000
7.750 1.3410 0.01152 0.00566 -0.0923 0.1928 1.0000
8.000 1.3470 0.01284 0.00656 -0.0889 0.1261 1.0000
8.250 1.3615 0.01356 0.00716 -0.0868 0.1065 1.0000
8.500 1.3771 0.01417 0.00769 -0.0850 0.0863 1.0000
8.750 1.3743 0.01561 0.00880 -0.0800 0.0353 1.0000
9.000 1.3779 0.01654 0.00962 -0.0761 0.0179 1.0000
9.250 1.3889 0.01717 0.01029 -0.0734 0.0156 1.0000
9.500 1.4005 0.01780 0.01097 -0.0710 0.0142 1.0000
9.750 1.4129 0.01842 0.01164 -0.0688 0.0136 1.0000
10.000 1.4240 0.01912 0.01240 -0.0666 0.0128 1.0000
10.250 1.4330 0.01998 0.01331 -0.0642 0.0121 1.0000
10.500 1.4387 0.02108 0.01448 -0.0616 0.0114 1.0000
10.750 1.4426 0.02237 0.01587 -0.0590 0.0109 1.0000
11.000 1.4523 0.02337 0.01692 -0.0573 0.0107 1.0000
11.250 1.4612 0.02448 0.01809 -0.0556 0.0103 1.0000
11.500 1.4680 0.02581 0.01949 -0.0539 0.0100 1.0000
11.750 1.4732 0.02733 0.02109 -0.0523 0.0097 1.0000
12.000 1.4791 0.02888 0.02270 -0.0509 0.0094 1.0000
12.250 1.4822 0.03076 0.02466 -0.0495 0.0091 1.0000
12.500 1.4850 0.03275 0.02673 -0.0483 0.0089 1.0000
12.750 1.4826 0.03536 0.02943 -0.0472 0.0086 1.0000
13.000 1.4803 0.03807 0.03222 -0.0463 0.0084 1.0000
13.250 1.4680 0.04197 0.03626 -0.0454 0.0082 1.0000
13.500 1.4642 0.04507 0.03945 -0.0449 0.0080 1.0000
13.750 1.4657 0.04767 0.04213 -0.0446 0.0079 1.0000
14.000 1.4689 0.05012 0.04465 -0.0444 0.0078 1.0000
14.250 1.4668 0.05325 0.04787 -0.0442 0.0077 1.0000
14.500 1.4648 0.05643 0.05114 -0.0442 0.0075 1.0000
14.750 1.4611 0.05992 0.05472 -0.0443 0.0074 1.0000
15.000 1.4586 0.06336 0.05825 -0.0446 0.0073 1.0000
15.250 1.4562 0.06685 0.06182 -0.0450 0.0072 1.0000
15.500 1.4521 0.07067 0.06572 -0.0455 0.0070 1.0000
15.750 1.4508 0.07421 0.06935 -0.0461 0.0068 1.0000
16.000 1.4458 0.07833 0.07355 -0.0469 0.0067 1.0000
16.250 1.4427 0.08224 0.07755 -0.0478 0.0067 1.0000
16.500 1.4398 0.08623 0.08161 -0.0487 0.0065 1.0000
16.750 1.4352 0.09051 0.08597 -0.0498 0.0065 1.0000
17.000 1.4319 0.09467 0.09019 -0.0511 0.0063 1.0000
17.250 1.4283 0.09886 0.09446 -0.0523 0.0063 1.0000
17.500 1.4238 0.10325 0.09893 -0.0537 0.0062 1.0000
17.750 1.4195 0.10760 0.10335 -0.0550 0.0061 1.0000
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