GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 500,000 Max Cl/Cd: 114.6 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe529-il-500000.txt Download as CSV file: xf-goe529-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2511 0.10715 0.10495 -0.0364 1.0000 0.0210
-9.500 -0.2560 0.10445 0.10230 -0.0383 1.0000 0.0217
-9.250 -0.2614 0.10207 0.09996 -0.0387 1.0000 0.0218
-9.000 -0.2564 0.09861 0.09653 -0.0413 0.9987 0.0219
-8.750 -0.2389 0.09398 0.09190 -0.0468 0.9928 0.0220
-8.500 -0.2217 0.08988 0.08780 -0.0468 0.9887 0.0226
-8.250 -0.2023 0.08646 0.08438 -0.0505 0.9814 0.0230
-8.000 -0.1819 0.08325 0.08116 -0.0546 0.9719 0.0242
-7.750 -0.1593 0.07897 0.07686 -0.0611 0.9609 0.0257
-7.500 -0.0753 0.05501 0.05268 -0.0794 0.8628 0.0276
-7.250 -0.0715 0.05210 0.04968 -0.0781 0.8386 0.0281
-7.000 -0.0872 0.06158 0.05921 -0.0917 0.8900 0.0281
-6.750 -0.0719 0.05988 0.05738 -0.0917 0.8629 0.0287
-6.500 -0.0590 0.05802 0.05537 -0.0923 0.8363 0.0297
-6.250 -0.0467 0.05536 0.05258 -0.0942 0.8121 0.0310
-6.000 -0.0239 0.05009 0.04706 -0.1020 0.7912 0.0341
-5.750 -0.0143 0.04310 0.03985 -0.1058 0.7746 0.0348
-5.500 0.0012 0.04160 0.03826 -0.1054 0.7583 0.0356
-5.250 0.0199 0.04020 0.03675 -0.1054 0.7435 0.0365
-5.000 0.0405 0.03834 0.03477 -0.1060 0.7305 0.0382
-4.750 0.0648 0.03077 0.02666 -0.1098 0.7206 0.0439
-4.500 0.0860 0.02984 0.02567 -0.1095 0.7107 0.0448
-4.250 0.1086 0.02875 0.02447 -0.1094 0.7016 0.0462
-4.000 0.1300 0.02056 0.01524 -0.1096 0.6955 0.0434
-3.750 0.1521 0.01736 0.01169 -0.1091 0.6884 0.0397
-3.500 0.1768 0.01536 0.00927 -0.1085 0.6823 0.0395
-3.250 0.2030 0.01442 0.00809 -0.1081 0.6759 0.0406
-3.000 0.2293 0.01355 0.00697 -0.1077 0.6702 0.0411
-2.750 0.2561 0.01284 0.00610 -0.1074 0.6644 0.0415
-2.500 0.2829 0.01229 0.00541 -0.1070 0.6588 0.0420
-2.250 0.3099 0.01192 0.00490 -0.1067 0.6539 0.0426
-2.000 0.3363 0.01116 0.00406 -0.1064 0.6488 0.0440
-1.750 0.3628 0.01074 0.00359 -0.1060 0.6435 0.0454
-1.500 0.3896 0.01052 0.00330 -0.1057 0.6386 0.0468
-1.250 0.4167 0.01030 0.00308 -0.1054 0.6336 0.0485
-1.000 0.4437 0.01014 0.00288 -0.1051 0.6285 0.0505
-0.750 0.4708 0.01006 0.00273 -0.1048 0.6236 0.0527
-0.500 0.4976 0.00983 0.00255 -0.1046 0.6183 0.0589
-0.250 0.5246 0.00970 0.00244 -0.1043 0.6131 0.0704
0.000 0.5514 0.00962 0.00240 -0.1040 0.6080 0.1019
0.250 0.5784 0.00952 0.00238 -0.1038 0.6023 0.1253
0.500 0.6053 0.00947 0.00238 -0.1035 0.5966 0.1510
0.750 0.6320 0.00942 0.00240 -0.1033 0.5908 0.1866
1.000 0.6578 0.00916 0.00242 -0.1030 0.5836 0.2809
1.250 0.7048 0.00764 0.00252 -0.1074 0.5745 1.0000
1.500 0.7303 0.00769 0.00250 -0.1069 0.5660 1.0000
1.750 0.7559 0.00776 0.00250 -0.1063 0.5577 1.0000
2.000 0.7814 0.00783 0.00250 -0.1057 0.5491 1.0000
2.250 0.8073 0.00789 0.00253 -0.1053 0.5403 1.0000
2.500 0.8327 0.00800 0.00256 -0.1047 0.5322 1.0000
2.750 0.8586 0.00807 0.00261 -0.1043 0.5227 1.0000
3.000 0.8842 0.00817 0.00266 -0.1038 0.5132 1.0000
3.250 0.9093 0.00830 0.00273 -0.1032 0.5031 1.0000
3.500 0.9348 0.00842 0.00281 -0.1027 0.4922 1.0000
3.750 0.9600 0.00856 0.00291 -0.1022 0.4818 1.0000
4.000 0.9848 0.00873 0.00303 -0.1016 0.4722 1.0000
4.250 1.0098 0.00890 0.00317 -0.1011 0.4624 1.0000
4.500 1.0348 0.00908 0.00331 -0.1006 0.4534 1.0000
5.000 1.0843 0.00947 0.00366 -0.0995 0.4359 1.0000
5.250 1.1087 0.00969 0.00384 -0.0989 0.4274 1.0000
5.500 1.1334 0.00989 0.00404 -0.0984 0.4194 1.0000
5.750 1.1578 0.01011 0.00425 -0.0978 0.4119 1.0000
6.000 1.1814 0.01035 0.00447 -0.0971 0.4013 1.0000
6.250 1.2046 0.01060 0.00468 -0.0964 0.3869 1.0000
6.500 1.2282 0.01083 0.00490 -0.0957 0.3743 1.0000
6.750 1.2516 0.01107 0.00513 -0.0950 0.3628 1.0000
7.000 1.2745 0.01134 0.00539 -0.0942 0.3506 1.0000
7.250 1.2967 0.01163 0.00566 -0.0934 0.3360 1.0000
7.500 1.3185 0.01195 0.00595 -0.0924 0.3203 1.0000
7.750 1.3393 0.01231 0.00627 -0.0913 0.3032 1.0000
8.000 1.3580 0.01279 0.00667 -0.0899 0.2826 1.0000
8.250 1.3762 0.01329 0.00709 -0.0885 0.2602 1.0000
8.500 1.3914 0.01395 0.00762 -0.0866 0.2338 1.0000
8.750 1.4022 0.01483 0.00829 -0.0840 0.1986 1.0000
9.000 1.4005 0.01623 0.00930 -0.0795 0.1364 1.0000
9.250 1.4007 0.01741 0.01032 -0.0752 0.1097 1.0000
9.500 1.3996 0.01872 0.01142 -0.0711 0.0703 1.0000
9.750 1.3906 0.02054 0.01300 -0.0662 0.0357 1.0000
10.000 1.3914 0.02194 0.01433 -0.0629 0.0230 1.0000
10.250 1.3970 0.02315 0.01557 -0.0605 0.0203 1.0000
10.500 1.4023 0.02446 0.01696 -0.0582 0.0187 1.0000
10.750 1.4093 0.02572 0.01832 -0.0563 0.0180 1.0000
11.000 1.4143 0.02721 0.01992 -0.0544 0.0171 1.0000
11.250 1.4170 0.02897 0.02177 -0.0527 0.0162 1.0000
11.500 1.4172 0.03105 0.02394 -0.0510 0.0155 1.0000
11.750 1.4157 0.03342 0.02641 -0.0495 0.0151 1.0000
12.000 1.4095 0.03638 0.02950 -0.0481 0.0146 1.0000
12.250 1.4069 0.03915 0.03238 -0.0471 0.0143 1.0000
12.500 1.4073 0.04171 0.03504 -0.0465 0.0141 1.0000
12.750 1.4058 0.04456 0.03800 -0.0459 0.0138 1.0000
13.000 1.4044 0.04745 0.04099 -0.0454 0.0136 1.0000
13.250 1.4006 0.05072 0.04436 -0.0451 0.0133 1.0000
13.500 1.3969 0.05403 0.04777 -0.0449 0.0131 1.0000
13.750 1.3931 0.05744 0.05128 -0.0448 0.0129 1.0000
14.000 1.3899 0.06089 0.05483 -0.0449 0.0127 1.0000
14.250 1.3867 0.06440 0.05842 -0.0451 0.0125 1.0000
14.500 1.3831 0.06802 0.06213 -0.0453 0.0123 1.0000
14.750 1.3808 0.07157 0.06576 -0.0456 0.0121 1.0000
15.000 1.3785 0.07514 0.06940 -0.0460 0.0118 1.0000
15.250 1.3761 0.07872 0.07302 -0.0465 0.0115 1.0000
15.500 1.3735 0.08207 0.07641 -0.0463 0.0112 1.0000
15.750 1.3752 0.08471 0.07911 -0.0457 0.0109 1.0000
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