GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 200,000 Max Cl/Cd: 72.55 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe257-il-200000-n5.txt Download as CSV file: xf-goe257-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3849 0.09403 0.09072 -0.0184 1.0000 0.0210
-7.750 -0.3826 0.09083 0.08757 -0.0198 1.0000 0.0214
-7.500 -0.3789 0.08747 0.08425 -0.0220 1.0000 0.0218
-7.000 -0.3550 0.07903 0.07581 -0.0363 1.0000 0.0252
-6.750 -0.3418 0.07456 0.07131 -0.0406 1.0000 0.0253
-6.500 -0.3287 0.07011 0.06682 -0.0437 0.9992 0.0253
-6.000 -0.2781 0.05938 0.05589 -0.0537 0.9787 0.0248
-5.750 -0.2484 0.05373 0.05008 -0.0598 0.9657 0.0266
-5.500 -0.2228 0.05145 0.04774 -0.0622 0.9505 0.0296
-5.250 -0.1764 0.04691 0.04263 -0.0684 0.9342 0.0338
-4.750 -0.1315 0.03856 0.03398 -0.0720 0.8926 0.0362
-4.500 -0.1078 0.03654 0.03177 -0.0725 0.8652 0.0391
-4.250 -0.0803 0.03351 0.02836 -0.0731 0.8372 0.0401
-4.000 -0.0521 0.03027 0.02466 -0.0736 0.8112 0.0387
-3.750 -0.0243 0.02821 0.02219 -0.0737 0.7893 0.0412
-3.500 0.0055 0.02506 0.01846 -0.0739 0.7725 0.0374
-3.250 0.0356 0.02268 0.01547 -0.0738 0.7583 0.0359
-3.000 0.0627 0.02171 0.01428 -0.0740 0.7454 0.0376
-2.750 0.0914 0.02052 0.01277 -0.0741 0.7341 0.0384
-2.500 0.1208 0.01917 0.01105 -0.0742 0.7243 0.0374
-2.250 0.1497 0.01817 0.00974 -0.0742 0.7156 0.0371
-2.000 0.1785 0.01734 0.00868 -0.0743 0.7073 0.0372
-1.750 0.2071 0.01666 0.00782 -0.0743 0.6997 0.0374
-1.500 0.2356 0.01607 0.00711 -0.0744 0.6917 0.0378
-1.250 0.2639 0.01565 0.00659 -0.0745 0.6843 0.0395
-1.000 0.2923 0.01522 0.00609 -0.0746 0.6763 0.0405
-0.750 0.3207 0.01479 0.00560 -0.0747 0.6689 0.0403
-0.500 0.3491 0.01441 0.00518 -0.0748 0.6613 0.0402
-0.250 0.3776 0.01411 0.00484 -0.0749 0.6542 0.0402
0.000 0.4060 0.01385 0.00456 -0.0751 0.6466 0.0404
0.250 0.4345 0.01364 0.00432 -0.0753 0.6384 0.0407
0.500 0.4629 0.01350 0.00411 -0.0754 0.6289 0.0413
0.750 0.4914 0.01338 0.00395 -0.0756 0.6178 0.0421
1.000 0.5198 0.01331 0.00381 -0.0757 0.6071 0.0432
1.250 0.5481 0.01328 0.00370 -0.0758 0.5969 0.0444
1.500 0.5765 0.01323 0.00363 -0.0759 0.5858 0.0479
1.750 0.6049 0.01319 0.00363 -0.0761 0.5750 0.0566
2.000 0.6285 0.01098 0.00360 -0.0755 0.5645 1.0000
2.250 0.6566 0.01110 0.00361 -0.0755 0.5518 1.0000
2.500 0.6846 0.01123 0.00366 -0.0756 0.5391 1.0000
2.750 0.7126 0.01137 0.00373 -0.0757 0.5266 1.0000
3.000 0.7405 0.01152 0.00381 -0.0758 0.5130 1.0000
3.250 0.7681 0.01169 0.00391 -0.0758 0.4985 1.0000
3.500 0.7956 0.01187 0.00403 -0.0759 0.4845 1.0000
3.750 0.8230 0.01208 0.00417 -0.0759 0.4705 1.0000
4.000 0.8503 0.01231 0.00436 -0.0759 0.4562 1.0000
4.250 0.8774 0.01256 0.00456 -0.0759 0.4421 1.0000
4.500 0.9045 0.01281 0.00478 -0.0760 0.4292 1.0000
4.750 0.9315 0.01307 0.00504 -0.0760 0.4163 1.0000
5.000 0.9583 0.01334 0.00531 -0.0760 0.4013 1.0000
5.250 0.9851 0.01361 0.00559 -0.0759 0.3864 1.0000
5.500 1.0113 0.01394 0.00588 -0.0759 0.3626 1.0000
5.750 1.0356 0.01446 0.00620 -0.0756 0.3037 1.0000
6.000 1.0577 0.01535 0.00672 -0.0752 0.2470 1.0000
6.250 1.0814 0.01601 0.00728 -0.0749 0.2211 1.0000
6.500 1.1050 0.01667 0.00785 -0.0746 0.1960 1.0000
6.750 1.1288 0.01727 0.00843 -0.0742 0.1728 1.0000
7.000 1.1430 0.01915 0.00962 -0.0730 0.0651 1.0000
7.250 1.1631 0.02019 0.01061 -0.0721 0.0385 1.0000
7.500 1.1828 0.02123 0.01154 -0.0711 0.0216 1.0000
7.750 1.2039 0.02204 0.01248 -0.0703 0.0189 1.0000
8.000 1.2235 0.02297 0.01357 -0.0692 0.0167 1.0000
8.250 1.2408 0.02406 0.01483 -0.0679 0.0150 1.0000
8.500 1.2550 0.02538 0.01634 -0.0661 0.0140 1.0000
8.750 1.2654 0.02689 0.01802 -0.0639 0.0134 1.0000
9.000 1.2763 0.02818 0.01946 -0.0617 0.0130 1.0000
9.250 1.2849 0.02954 0.02096 -0.0593 0.0126 1.0000
9.500 1.2909 0.03094 0.02248 -0.0565 0.0120 1.0000
9.750 1.2938 0.03244 0.02414 -0.0534 0.0114 1.0000
10.000 1.2965 0.03415 0.02597 -0.0508 0.0109 1.0000
10.250 1.2985 0.03611 0.02804 -0.0485 0.0105 1.0000
10.500 1.3006 0.03823 0.03029 -0.0465 0.0103 1.0000
10.750 1.3029 0.04049 0.03266 -0.0448 0.0100 1.0000
11.000 1.3054 0.04287 0.03516 -0.0433 0.0098 1.0000
11.250 1.3079 0.04537 0.03776 -0.0420 0.0096 1.0000
11.500 1.3107 0.04794 0.04044 -0.0407 0.0094 1.0000
11.750 1.3137 0.05063 0.04323 -0.0394 0.0092 1.0000
12.000 1.3176 0.05341 0.04615 -0.0381 0.0090 1.0000
12.250 1.3219 0.05643 0.04931 -0.0365 0.0089 1.0000
12.500 1.3229 0.05961 0.05268 -0.0357 0.0087 1.0000
12.750 1.3213 0.06282 0.05613 -0.0354 0.0086 1.0000
13.000 1.3182 0.06629 0.05984 -0.0354 0.0085 1.0000
13.250 1.3136 0.07007 0.06386 -0.0357 0.0083 1.0000
13.500 1.3074 0.07418 0.06820 -0.0362 0.0081 1.0000
13.750 1.2996 0.07858 0.07283 -0.0370 0.0079 1.0000
14.000 1.2902 0.08335 0.07782 -0.0381 0.0078 1.0000
14.250 1.2796 0.08850 0.08318 -0.0396 0.0077 1.0000
14.500 1.2678 0.09406 0.08896 -0.0415 0.0076 1.0000
14.750 1.2550 0.10007 0.09518 -0.0439 0.0076 1.0000
15.000 1.2414 0.10654 0.10185 -0.0468 0.0076 1.0000
15.250 1.2273 0.11344 0.10895 -0.0503 0.0076 1.0000
15.500 1.2127 0.12080 0.11650 -0.0543 0.0076 1.0000
15.750 1.1979 0.12859 0.12448 -0.0588 0.0076 1.0000
16.000 1.1829 0.13689 0.13295 -0.0638 0.0077 1.0000
16.250 1.1679 0.14572 0.14195 -0.0693 0.0077 1.0000
16.500 1.1527 0.15524 0.15161 -0.0754 0.0078 1.0000
16.750 1.1373 0.16547 0.16198 -0.0820 0.0079 1.0000
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Polar data table (+)
Polar graphs
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