GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 500,000 Max Cl/Cd: 101.37 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe389-il-500000.txt Download as CSV file: xf-goe389-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3526 0.09310 0.09086 -0.0332 1.0000 0.0264
-8.750 -0.3526 0.08956 0.08735 -0.0349 1.0000 0.0278
-8.500 -0.3638 0.08501 0.08287 -0.0385 1.0000 0.0292
-8.250 -0.3051 0.06502 0.06309 -0.0456 0.9958 0.0300
-8.000 -0.2917 0.06136 0.05942 -0.0480 0.9924 0.0305
-7.750 -0.3633 0.07054 0.06848 -0.0520 0.9941 0.0295
-7.500 -0.3523 0.06118 0.05908 -0.0623 0.9874 0.0304
-7.250 -0.3252 0.05847 0.05633 -0.0665 0.9841 0.0312
-7.000 -0.2990 0.05515 0.05296 -0.0714 0.9777 0.0326
-6.750 -0.2600 0.04342 0.04060 -0.0868 0.9696 0.0374
-6.500 -0.2467 0.03511 0.03206 -0.0914 0.9599 0.0391
-6.250 -0.2195 0.03360 0.03051 -0.0928 0.9511 0.0403
-6.000 -0.1908 0.03146 0.02821 -0.0947 0.9427 0.0426
-5.750 -0.1681 0.02340 0.01903 -0.0956 0.9305 0.0371
-5.500 -0.1419 0.02190 0.01719 -0.0955 0.9184 0.0374
-5.250 -0.1182 0.01926 0.01415 -0.0953 0.9060 0.0376
-5.000 -0.0935 0.01722 0.01178 -0.0949 0.8941 0.0377
-4.750 -0.0679 0.01567 0.00997 -0.0945 0.8830 0.0378
-4.500 -0.0424 0.01416 0.00823 -0.0941 0.8713 0.0382
-4.250 -0.0166 0.01300 0.00694 -0.0937 0.8593 0.0393
-4.000 0.0099 0.01236 0.00621 -0.0933 0.8477 0.0402
-3.750 0.0367 0.01179 0.00555 -0.0930 0.8364 0.0408
-3.250 0.0905 0.01088 0.00447 -0.0923 0.8124 0.0423
-3.000 0.1175 0.01050 0.00402 -0.0920 0.8006 0.0431
-2.750 0.1447 0.01020 0.00364 -0.0917 0.7897 0.0443
-2.500 0.1720 0.00997 0.00332 -0.0915 0.7790 0.0458
-2.250 0.1993 0.00976 0.00302 -0.0912 0.7680 0.0468
-2.000 0.2265 0.00943 0.00263 -0.0910 0.7576 0.0489
-1.750 0.2540 0.00925 0.00240 -0.0908 0.7478 0.0523
-1.500 0.2816 0.00915 0.00225 -0.0906 0.7375 0.0566
-1.250 0.3092 0.00898 0.00208 -0.0904 0.7270 0.0702
-1.000 0.3359 0.00853 0.00193 -0.0903 0.7168 0.1685
-0.750 0.3626 0.00824 0.00192 -0.0902 0.7059 0.2795
-0.500 0.3896 0.00802 0.00190 -0.0901 0.6937 0.3535
-0.250 0.4151 0.00755 0.00192 -0.0898 0.6796 0.5265
0.000 0.4385 0.00703 0.00193 -0.0889 0.6632 0.7071
0.250 0.4750 0.00651 0.00194 -0.0900 0.6401 0.9954
0.500 0.5027 0.00662 0.00189 -0.0899 0.6097 1.0000
0.750 0.5275 0.00682 0.00187 -0.0892 0.5732 1.0000
1.000 0.5521 0.00708 0.00190 -0.0885 0.5411 1.0000
1.250 0.5774 0.00732 0.00198 -0.0880 0.5168 1.0000
1.500 0.6031 0.00755 0.00206 -0.0876 0.4985 1.0000
1.750 0.6292 0.00775 0.00215 -0.0872 0.4839 1.0000
2.000 0.6558 0.00792 0.00224 -0.0870 0.4724 1.0000
2.250 0.6824 0.00810 0.00235 -0.0867 0.4628 1.0000
2.500 0.7089 0.00828 0.00245 -0.0865 0.4537 1.0000
2.750 0.7359 0.00843 0.00256 -0.0863 0.4457 1.0000
3.000 0.7624 0.00862 0.00269 -0.0860 0.4379 1.0000
3.250 0.7894 0.00876 0.00282 -0.0859 0.4312 1.0000
3.500 0.8161 0.00893 0.00295 -0.0857 0.4246 1.0000
3.750 0.8429 0.00910 0.00311 -0.0855 0.4182 1.0000
4.000 0.8695 0.00926 0.00324 -0.0853 0.4097 1.0000
4.250 0.8962 0.00941 0.00338 -0.0851 0.4008 1.0000
4.500 0.9223 0.00961 0.00353 -0.0848 0.3922 1.0000
4.750 0.9492 0.00974 0.00368 -0.0846 0.3832 1.0000
5.000 0.9754 0.00991 0.00383 -0.0844 0.3724 1.0000
5.250 1.0013 0.01011 0.00398 -0.0841 0.3617 1.0000
5.500 1.0278 0.01026 0.00415 -0.0839 0.3503 1.0000
5.750 1.0538 0.01045 0.00432 -0.0836 0.3373 1.0000
6.000 1.0796 0.01065 0.00451 -0.0833 0.3250 1.0000
6.250 1.1048 0.01091 0.00472 -0.0830 0.3079 1.0000
6.500 1.1287 0.01127 0.00498 -0.0824 0.2804 1.0000
6.750 1.1503 0.01185 0.00534 -0.0816 0.2397 1.0000
7.000 1.1676 0.01286 0.00596 -0.0801 0.1727 1.0000
7.250 1.1835 0.01403 0.00677 -0.0785 0.1190 1.0000
7.500 1.2039 0.01472 0.00736 -0.0775 0.0978 1.0000
7.750 1.2194 0.01585 0.00817 -0.0758 0.0503 1.0000
8.000 1.2351 0.01691 0.00905 -0.0741 0.0219 1.0000
8.250 1.2555 0.01750 0.00969 -0.0730 0.0189 1.0000
8.500 1.2749 0.01815 0.01041 -0.0717 0.0176 1.0000
8.750 1.2929 0.01888 0.01123 -0.0703 0.0166 1.0000
9.000 1.3084 0.01976 0.01221 -0.0685 0.0157 1.0000
9.250 1.3227 0.02066 0.01321 -0.0665 0.0151 1.0000
9.500 1.3356 0.02146 0.01409 -0.0643 0.0146 1.0000
9.750 1.3458 0.02240 0.01511 -0.0618 0.0141 1.0000
10.000 1.3541 0.02347 0.01628 -0.0592 0.0137 1.0000
10.250 1.3609 0.02468 0.01758 -0.0566 0.0134 1.0000
10.500 1.3660 0.02606 0.01906 -0.0541 0.0131 1.0000
10.750 1.3693 0.02766 0.02074 -0.0517 0.0128 1.0000
11.000 1.3710 0.02951 0.02267 -0.0494 0.0126 1.0000
11.250 1.3712 0.03159 0.02485 -0.0474 0.0124 1.0000
11.500 1.3698 0.03397 0.02731 -0.0456 0.0122 1.0000
11.750 1.3671 0.03661 0.03004 -0.0440 0.0120 1.0000
12.000 1.3643 0.03938 0.03289 -0.0426 0.0119 1.0000
12.250 1.3621 0.04216 0.03575 -0.0411 0.0117 1.0000
12.500 1.3612 0.04484 0.03848 -0.0392 0.0116 1.0000
12.750 1.3662 0.04703 0.04078 -0.0386 0.0115 1.0000
13.000 1.3705 0.04933 0.04320 -0.0382 0.0113 1.0000
13.250 1.3740 0.05176 0.04575 -0.0378 0.0111 1.0000
13.500 1.3767 0.05430 0.04840 -0.0374 0.0109 1.0000
13.750 1.3786 0.05693 0.05114 -0.0369 0.0107 1.0000
14.000 1.3803 0.05963 0.05394 -0.0363 0.0106 1.0000
14.250 1.3818 0.06241 0.05684 -0.0358 0.0106 1.0000
14.500 1.3826 0.06533 0.05988 -0.0354 0.0105 1.0000
14.750 1.3827 0.06840 0.06309 -0.0352 0.0104 1.0000
15.000 1.3818 0.07169 0.06651 -0.0352 0.0104 1.0000
15.250 1.3799 0.07520 0.07015 -0.0353 0.0104 1.0000
15.500 1.3766 0.07897 0.07407 -0.0356 0.0104 1.0000
15.750 1.3719 0.08304 0.07830 -0.0362 0.0104 1.0000
16.000 1.3657 0.08745 0.08287 -0.0371 0.0104 1.0000
16.250 1.3582 0.09219 0.08777 -0.0384 0.0104 1.0000
16.500 1.3490 0.09728 0.09303 -0.0400 0.0105 1.0000
16.750 1.3386 0.10271 0.09863 -0.0418 0.0106 1.0000
17.000 1.3271 0.10849 0.10458 -0.0441 0.0107 1.0000
17.250 1.3146 0.11459 0.11084 -0.0468 0.0108 1.0000
17.500 1.3012 0.12096 0.11738 -0.0497 0.0109 1.0000
17.750 1.2867 0.12766 0.12423 -0.0528 0.0111 1.0000
18.500 1.0181 0.12804 0.12506 -0.0351 0.0117 1.0000
18.750 1.0030 0.13316 0.13030 -0.0385 0.0118 1.0000
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