GOE 526 AIRFOIL (goe526-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 526 AIRFOIL (goe526-il) Reynolds number: 500,000 Max Cl/Cd: 91.8 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe526-il-500000-n5.txt Download as CSV file: xf-goe526-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 526 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8973 0.03799 0.03439 -0.0968 1.0000 0.0276
-13.500 -0.9276 0.03580 0.03208 -0.0917 1.0000 0.0276
-13.250 -0.9208 0.03286 0.02885 -0.0930 0.9948 0.0279
-13.000 -0.9065 0.03063 0.02643 -0.0940 0.9886 0.0282
-12.750 -0.8866 0.02894 0.02463 -0.0949 0.9840 0.0285
-12.500 -0.8655 0.02763 0.02321 -0.0955 0.9794 0.0287
-12.250 -0.8432 0.02646 0.02194 -0.0959 0.9744 0.0290
-12.000 -0.8167 0.02531 0.02068 -0.0970 0.9710 0.0293
-11.750 -0.7924 0.02428 0.01954 -0.0974 0.9656 0.0297
-11.500 -0.7657 0.02331 0.01845 -0.0982 0.9605 0.0301
-11.250 -0.7364 0.02237 0.01738 -0.0994 0.9566 0.0306
-11.000 -0.7124 0.02145 0.01633 -0.0994 0.9495 0.0310
-10.750 -0.6849 0.02052 0.01524 -0.1000 0.9432 0.0313
-10.500 -0.6593 0.01970 0.01426 -0.1001 0.9354 0.0317
-10.250 -0.6327 0.01896 0.01337 -0.1003 0.9267 0.0320
-10.000 -0.6087 0.01822 0.01252 -0.0999 0.9169 0.0324
-9.750 -0.5837 0.01753 0.01174 -0.0997 0.9075 0.0328
-9.500 -0.5602 0.01701 0.01115 -0.0990 0.8964 0.0332
-9.250 -0.5355 0.01656 0.01062 -0.0985 0.8859 0.0337
-9.000 -0.5110 0.01614 0.01010 -0.0979 0.8748 0.0341
-8.750 -0.4870 0.01572 0.00958 -0.0972 0.8645 0.0347
-8.500 -0.4627 0.01531 0.00906 -0.0965 0.8551 0.0352
-8.250 -0.4388 0.01491 0.00856 -0.0957 0.8455 0.0357
-8.000 -0.4144 0.01453 0.00806 -0.0950 0.8369 0.0362
-7.750 -0.3900 0.01418 0.00761 -0.0942 0.8280 0.0366
-7.500 -0.3658 0.01380 0.00715 -0.0935 0.8205 0.0372
-7.250 -0.3414 0.01344 0.00675 -0.0927 0.8133 0.0378
-7.000 -0.3164 0.01315 0.00640 -0.0921 0.8063 0.0385
-6.750 -0.2910 0.01289 0.00609 -0.0915 0.7999 0.0393
-6.500 -0.2655 0.01265 0.00579 -0.0909 0.7932 0.0402
-6.250 -0.2398 0.01242 0.00548 -0.0904 0.7874 0.0412
-6.000 -0.2139 0.01219 0.00519 -0.0898 0.7821 0.0420
-5.750 -0.1888 0.01189 0.00488 -0.0892 0.7754 0.0430
-5.500 -0.1632 0.01169 0.00462 -0.0886 0.7684 0.0442
-5.250 -0.1374 0.01149 0.00439 -0.0880 0.7609 0.0456
-5.000 -0.1115 0.01131 0.00416 -0.0875 0.7538 0.0470
-4.750 -0.0856 0.01113 0.00393 -0.0869 0.7473 0.0485
-4.500 -0.0597 0.01094 0.00373 -0.0864 0.7404 0.0504
-4.250 -0.0337 0.01080 0.00354 -0.0858 0.7334 0.0527
-4.000 -0.0075 0.01065 0.00337 -0.0853 0.7265 0.0550
-3.750 0.0184 0.01049 0.00320 -0.0848 0.7192 0.0577
-3.500 0.0447 0.01038 0.00305 -0.0842 0.7134 0.0607
-3.250 0.0712 0.01023 0.00291 -0.0838 0.7077 0.0638
-3.000 0.0975 0.01011 0.00279 -0.0833 0.7019 0.0678
-2.500 0.1504 0.00989 0.00258 -0.0824 0.6908 0.0783
-2.250 0.1766 0.00978 0.00249 -0.0819 0.6843 0.0848
-2.000 0.2029 0.00971 0.00240 -0.0814 0.6786 0.0920
-1.750 0.2295 0.00962 0.00235 -0.0810 0.6727 0.1012
-1.500 0.2557 0.00954 0.00231 -0.0805 0.6658 0.1111
-1.250 0.2820 0.00949 0.00226 -0.0801 0.6592 0.1201
-1.000 0.3084 0.00944 0.00223 -0.0796 0.6512 0.1292
-0.750 0.3343 0.00941 0.00219 -0.0790 0.6438 0.1374
-0.500 0.3608 0.00937 0.00217 -0.0786 0.6357 0.1451
-0.250 0.3864 0.00935 0.00214 -0.0779 0.6269 0.1534
0.000 0.4120 0.00933 0.00211 -0.0773 0.6143 0.1613
0.250 0.4367 0.00933 0.00209 -0.0765 0.5981 0.1702
0.500 0.4609 0.00936 0.00208 -0.0756 0.5799 0.1807
0.750 0.4846 0.00938 0.00209 -0.0747 0.5614 0.1961
1.000 0.5083 0.00940 0.00211 -0.0737 0.5439 0.2187
1.500 0.5526 0.00935 0.00222 -0.0713 0.5048 0.3209
1.750 0.5690 0.00900 0.00233 -0.0692 0.4848 0.5092
2.000 0.5753 0.00829 0.00242 -0.0646 0.4687 0.7910
2.250 0.6407 0.00850 0.00283 -0.0723 0.4444 0.9521
2.500 0.6805 0.00877 0.00301 -0.0748 0.4287 0.9680
2.750 0.7192 0.00902 0.00317 -0.0771 0.4168 0.9769
3.000 0.7537 0.00924 0.00333 -0.0786 0.4070 0.9838
3.250 0.7964 0.00943 0.00348 -0.0818 0.3982 0.9906
3.750 0.8796 0.00981 0.00375 -0.0878 0.3803 0.9997
4.000 0.9014 0.00999 0.00389 -0.0866 0.3728 1.0000
4.250 0.9216 0.01013 0.00401 -0.0850 0.3656 1.0000
4.500 0.9411 0.01029 0.00414 -0.0833 0.3577 1.0000
4.750 0.9601 0.01047 0.00429 -0.0815 0.3489 1.0000
5.000 0.9780 0.01068 0.00445 -0.0796 0.3379 1.0000
5.250 0.9969 0.01086 0.00460 -0.0777 0.3276 1.0000
5.500 1.0145 0.01108 0.00478 -0.0757 0.3183 1.0000
5.750 1.0330 0.01127 0.00494 -0.0738 0.3085 1.0000
6.000 1.0503 0.01150 0.00513 -0.0718 0.2977 1.0000
6.250 1.0666 0.01177 0.00534 -0.0695 0.2845 1.0000
6.500 1.0820 0.01207 0.00558 -0.0671 0.2678 1.0000
6.750 1.0953 0.01245 0.00585 -0.0644 0.2454 1.0000
7.000 1.1055 0.01291 0.00618 -0.0611 0.2196 1.0000
7.250 1.1118 0.01343 0.00655 -0.0571 0.1946 1.0000
7.500 1.1213 0.01389 0.00693 -0.0538 0.1804 1.0000
7.750 1.1335 0.01430 0.00729 -0.0510 0.1710 1.0000
8.000 1.1469 0.01470 0.00767 -0.0485 0.1643 1.0000
8.250 1.1617 0.01508 0.00805 -0.0463 0.1585 1.0000
8.500 1.1756 0.01553 0.00848 -0.0440 0.1529 1.0000
8.750 1.1909 0.01593 0.00890 -0.0420 0.1479 1.0000
9.000 1.2066 0.01634 0.00932 -0.0402 0.1429 1.0000
9.250 1.2209 0.01684 0.00981 -0.0381 0.1374 1.0000
9.500 1.2363 0.01730 0.01029 -0.0364 0.1321 1.0000
9.750 1.2512 0.01782 0.01081 -0.0346 0.1251 1.0000
10.000 1.2655 0.01838 0.01137 -0.0328 0.1186 1.0000
10.250 1.2788 0.01903 0.01198 -0.0310 0.1099 1.0000
10.500 1.2915 0.01973 0.01266 -0.0292 0.1004 1.0000
10.750 1.3030 0.02053 0.01343 -0.0273 0.0926 1.0000
11.000 1.3136 0.02142 0.01429 -0.0255 0.0858 1.0000
11.250 1.3252 0.02227 0.01515 -0.0238 0.0811 1.0000
11.500 1.3355 0.02324 0.01613 -0.0222 0.0772 1.0000
11.750 1.3473 0.02415 0.01708 -0.0207 0.0744 1.0000
12.000 1.3584 0.02514 0.01810 -0.0193 0.0714 1.0000
12.250 1.3678 0.02627 0.01926 -0.0178 0.0685 1.0000
12.500 1.3773 0.02743 0.02045 -0.0164 0.0662 1.0000
12.750 1.3881 0.02853 0.02161 -0.0153 0.0640 1.0000
13.000 1.3973 0.02978 0.02291 -0.0141 0.0617 1.0000
13.250 1.4046 0.03121 0.02436 -0.0128 0.0597 1.0000
13.500 1.4123 0.03264 0.02584 -0.0117 0.0578 1.0000
13.750 1.4211 0.03401 0.02728 -0.0108 0.0558 1.0000
14.000 1.4282 0.03557 0.02888 -0.0098 0.0538 1.0000
14.250 1.4328 0.03738 0.03072 -0.0089 0.0517 1.0000
14.500 1.4386 0.03913 0.03253 -0.0080 0.0504 1.0000
14.750 1.4454 0.04084 0.03432 -0.0074 0.0489 1.0000
15.000 1.4505 0.04276 0.03630 -0.0067 0.0474 1.0000
15.250 1.4542 0.04485 0.03845 -0.0061 0.0462 1.0000
15.500 1.4558 0.04722 0.04087 -0.0057 0.0448 1.0000
15.750 1.4590 0.04949 0.04321 -0.0053 0.0437 1.0000
16.000 1.4624 0.05179 0.04560 -0.0051 0.0427 1.0000
16.250 1.4643 0.05430 0.04818 -0.0049 0.0415 1.0000
16.500 1.4647 0.05704 0.05100 -0.0049 0.0405 1.0000
16.750 1.4637 0.06003 0.05405 -0.0050 0.0393 1.0000
17.250 1.4612 0.06621 0.06040 -0.0055 0.0377 1.0000
17.500 1.4607 0.06930 0.06358 -0.0059 0.0366 1.0000
17.750 1.4581 0.07269 0.06706 -0.0064 0.0359 1.0000
18.000 1.4547 0.07627 0.07070 -0.0071 0.0348 1.0000
18.250 1.4497 0.08008 0.07460 -0.0079 0.0343 1.0000
18.500 1.4427 0.08421 0.07881 -0.0089 0.0334 1.0000
18.750 1.4392 0.08790 0.08260 -0.0098 0.0328 1.0000
19.000 1.4352 0.09168 0.08648 -0.0108 0.0322 1.0000
19.250 1.4303 0.09562 0.09050 -0.0119 0.0314 1.0000
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Polar data table (+)
Polar graphs
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