GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 500,000 Max Cl/Cd: 94.57 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe389-il-500000-n5.txt Download as CSV file: xf-goe389-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4357 0.14194 0.13951 -0.0134 1.0000 0.0077
-12.750 -0.4292 0.13888 0.13646 -0.0147 1.0000 0.0079
-10.250 -0.6959 0.02628 0.02289 -0.0820 0.9903 0.0135
-10.000 -0.6624 0.02685 0.02356 -0.0829 0.9878 0.0140
-9.750 -0.6269 0.02805 0.02490 -0.0837 0.9859 0.0144
-9.500 -0.5946 0.02884 0.02575 -0.0841 0.9823 0.0149
-9.250 -0.5677 0.02709 0.02378 -0.0858 0.9774 0.0158
-9.000 -0.5476 0.02282 0.01887 -0.0876 0.9702 0.0175
-8.750 -0.5195 0.02120 0.01698 -0.0889 0.9648 0.0183
-8.500 -0.4888 0.02112 0.01690 -0.0898 0.9586 0.0188
-8.250 -0.4560 0.02122 0.01701 -0.0909 0.9521 0.0194
-8.000 -0.4241 0.02100 0.01673 -0.0921 0.9435 0.0201
-7.750 -0.3929 0.02023 0.01579 -0.0933 0.9336 0.0211
-7.500 -0.3639 0.01933 0.01467 -0.0939 0.9222 0.0222
-7.250 -0.3365 0.01864 0.01377 -0.0941 0.9107 0.0232
-7.000 -0.3095 0.01813 0.01307 -0.0941 0.8994 0.0238
-6.750 -0.2827 0.01782 0.01260 -0.0939 0.8879 0.0242
-6.500 -0.2596 0.01597 0.01044 -0.0937 0.8758 0.0255
-6.250 -0.2338 0.01534 0.00968 -0.0935 0.8634 0.0262
-6.000 -0.2076 0.01485 0.00909 -0.0933 0.8504 0.0268
-5.750 -0.1813 0.01442 0.00853 -0.0930 0.8357 0.0276
-5.500 -0.1551 0.01390 0.00786 -0.0927 0.8193 0.0282
-5.250 -0.1288 0.01337 0.00715 -0.0923 0.8021 0.0287
-5.000 -0.1026 0.01288 0.00650 -0.0920 0.7841 0.0292
-4.750 -0.0762 0.01246 0.00592 -0.0916 0.7686 0.0297
-4.500 -0.0494 0.01213 0.00546 -0.0914 0.7569 0.0305
-4.250 -0.0224 0.01178 0.00499 -0.0912 0.7473 0.0311
-4.000 0.0048 0.01144 0.00455 -0.0910 0.7385 0.0315
-3.500 0.0594 0.01090 0.00383 -0.0907 0.7215 0.0323
-3.000 0.1146 0.01047 0.00327 -0.0905 0.7065 0.0328
-2.750 0.1420 0.01024 0.00295 -0.0904 0.6986 0.0333
-2.500 0.1697 0.01000 0.00266 -0.0903 0.6898 0.0339
-2.250 0.1974 0.00982 0.00242 -0.0902 0.6811 0.0347
-2.000 0.2252 0.00968 0.00223 -0.0901 0.6714 0.0357
-1.750 0.2530 0.00956 0.00208 -0.0901 0.6602 0.0374
-1.500 0.2807 0.00947 0.00195 -0.0900 0.6466 0.0391
-1.250 0.3082 0.00941 0.00183 -0.0898 0.6295 0.0410
-1.000 0.3353 0.00939 0.00172 -0.0896 0.6041 0.0451
-0.750 0.3609 0.00944 0.00166 -0.0891 0.5626 0.0641
-0.500 0.3864 0.00958 0.00163 -0.0887 0.5247 0.0800
-0.250 0.4124 0.00953 0.00164 -0.0885 0.5000 0.1329
0.000 0.4390 0.00948 0.00167 -0.0883 0.4822 0.1925
0.250 0.4658 0.00941 0.00173 -0.0883 0.4689 0.2581
0.500 0.4929 0.00941 0.00178 -0.0882 0.4579 0.2998
1.000 0.5460 0.00899 0.00194 -0.0881 0.4395 0.5298
1.250 0.5683 0.00840 0.00205 -0.0870 0.4312 0.7669
1.500 0.6023 0.00811 0.00213 -0.0879 0.4220 1.0000
1.750 0.6290 0.00826 0.00219 -0.0877 0.4137 1.0000
2.000 0.6562 0.00837 0.00226 -0.0875 0.4070 1.0000
2.250 0.6832 0.00851 0.00234 -0.0873 0.4008 1.0000
2.500 0.7102 0.00863 0.00243 -0.0872 0.3950 1.0000
2.750 0.7373 0.00876 0.00253 -0.0871 0.3886 1.0000
3.000 0.7641 0.00891 0.00263 -0.0869 0.3830 1.0000
3.250 0.7913 0.00903 0.00274 -0.0868 0.3761 1.0000
3.500 0.8178 0.00920 0.00286 -0.0865 0.3673 1.0000
3.750 0.8447 0.00934 0.00298 -0.0864 0.3582 1.0000
4.000 0.8714 0.00950 0.00311 -0.0862 0.3515 1.0000
4.250 0.8981 0.00965 0.00326 -0.0860 0.3431 1.0000
4.500 0.9245 0.00983 0.00341 -0.0858 0.3336 1.0000
4.750 0.9504 0.01005 0.00357 -0.0855 0.3179 1.0000
5.000 0.9757 0.01032 0.00376 -0.0852 0.2982 1.0000
5.250 1.0001 0.01068 0.00399 -0.0847 0.2713 1.0000
5.500 1.0223 0.01126 0.00433 -0.0840 0.2284 1.0000
5.750 1.0389 0.01244 0.00501 -0.0825 0.1426 1.0000
6.000 1.0600 0.01313 0.00554 -0.0816 0.1135 1.0000
6.250 1.0837 0.01356 0.00592 -0.0810 0.1008 1.0000
6.500 1.1068 0.01402 0.00631 -0.0804 0.0828 1.0000
6.750 1.1256 0.01490 0.00696 -0.0791 0.0460 1.0000
7.000 1.1441 0.01577 0.00768 -0.0778 0.0173 1.0000
7.250 1.1664 0.01625 0.00821 -0.0770 0.0140 1.0000
7.500 1.1891 0.01668 0.00869 -0.0762 0.0130 1.0000
7.750 1.2108 0.01717 0.00925 -0.0754 0.0119 1.0000
8.000 1.2312 0.01775 0.00989 -0.0743 0.0108 1.0000
8.250 1.2497 0.01847 0.01072 -0.0730 0.0099 1.0000
8.500 1.2697 0.01901 0.01132 -0.0719 0.0095 1.0000
8.750 1.2885 0.01961 0.01200 -0.0706 0.0091 1.0000
9.000 1.3058 0.02029 0.01275 -0.0692 0.0086 1.0000
9.250 1.3216 0.02100 0.01352 -0.0675 0.0082 1.0000
9.500 1.3347 0.02174 0.01432 -0.0654 0.0078 1.0000
9.750 1.3461 0.02261 0.01525 -0.0631 0.0074 1.0000
10.000 1.3523 0.02383 0.01657 -0.0604 0.0070 1.0000
10.250 1.3612 0.02492 0.01774 -0.0581 0.0068 1.0000
10.500 1.3702 0.02604 0.01895 -0.0561 0.0067 1.0000
10.750 1.3778 0.02733 0.02033 -0.0541 0.0065 1.0000
11.000 1.3840 0.02879 0.02189 -0.0522 0.0063 1.0000
11.250 1.3891 0.03043 0.02363 -0.0505 0.0061 1.0000
11.500 1.3930 0.03226 0.02555 -0.0489 0.0060 1.0000
11.750 1.3963 0.03426 0.02766 -0.0476 0.0058 1.0000
12.000 1.3984 0.03648 0.02998 -0.0465 0.0057 1.0000
12.250 1.4000 0.03889 0.03250 -0.0457 0.0056 1.0000
12.500 1.4007 0.04149 0.03520 -0.0450 0.0055 1.0000
12.750 1.4008 0.04425 0.03806 -0.0445 0.0054 1.0000
13.000 1.4000 0.04719 0.04109 -0.0442 0.0053 1.0000
13.250 1.3985 0.05027 0.04427 -0.0441 0.0052 1.0000
13.500 1.3953 0.05364 0.04774 -0.0441 0.0051 1.0000
13.750 1.3906 0.05731 0.05150 -0.0443 0.0050 1.0000
14.000 1.3840 0.06130 0.05559 -0.0446 0.0049 1.0000
14.250 1.3758 0.06560 0.05999 -0.0450 0.0048 1.0000
14.500 1.3736 0.06931 0.06382 -0.0457 0.0048 1.0000
14.750 1.3709 0.07313 0.06775 -0.0464 0.0047 1.0000
15.000 1.3675 0.07710 0.07184 -0.0472 0.0046 1.0000
15.250 1.3636 0.08119 0.07604 -0.0481 0.0045 1.0000
15.500 1.3592 0.08537 0.08033 -0.0491 0.0045 1.0000
15.750 1.3542 0.08962 0.08470 -0.0500 0.0044 1.0000
16.000 1.3494 0.09391 0.08909 -0.0511 0.0044 1.0000
16.250 1.3446 0.09827 0.09359 -0.0523 0.0043 1.0000
16.500 1.3395 0.10272 0.09815 -0.0535 0.0042 1.0000
16.750 1.3342 0.10723 0.10277 -0.0549 0.0042 1.0000
17.000 1.3287 0.11182 0.10747 -0.0564 0.0041 1.0000
17.250 1.3233 0.11649 0.11225 -0.0581 0.0041 1.0000
17.500 1.3178 0.12130 0.11717 -0.0599 0.0040 1.0000
17.750 1.3120 0.12623 0.12223 -0.0619 0.0040 1.0000
18.000 1.3060 0.13127 0.12738 -0.0642 0.0039 1.0000
18.250 1.2999 0.13642 0.13265 -0.0665 0.0039 1.0000
18.500 1.2935 0.14176 0.13811 -0.0692 0.0039 1.0000
18.750 1.2870 0.14728 0.14375 -0.0720 0.0038 1.0000
19.000 1.2803 0.15298 0.14957 -0.0752 0.0038 1.0000
19.250 1.2734 0.15888 0.15559 -0.0786 0.0038 1.0000
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