GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 200,000 Max Cl/Cd: 75.62 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe596-il-200000-n5.txt Download as CSV file: xf-goe596-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3566 0.09058 0.08702 -0.0405 1.0000 0.0365
-8.500 -0.3673 0.08774 0.08426 -0.0409 1.0000 0.0366
-8.250 -0.3796 0.08533 0.08193 -0.0399 1.0000 0.0366
-8.000 -0.3745 0.08257 0.07921 -0.0366 0.9996 0.0373
-7.750 -0.3546 0.07975 0.07638 -0.0382 0.9946 0.0383
-7.500 -0.3353 0.07545 0.07207 -0.0439 0.9861 0.0390
-7.250 -0.3160 0.06721 0.06372 -0.0566 0.9746 0.0356
-7.000 -0.2950 0.06033 0.05671 -0.0657 0.9642 0.0359
-6.750 -0.2735 0.05507 0.05132 -0.0712 0.9557 0.0356
-6.500 -0.2501 0.05004 0.04613 -0.0762 0.9479 0.0350
-6.250 -0.2290 0.04492 0.04078 -0.0800 0.9374 0.0346
-6.000 -0.2051 0.03942 0.03493 -0.0837 0.9286 0.0348
-5.750 -0.1827 0.03429 0.02928 -0.0857 0.9186 0.0356
-5.500 -0.1601 0.03089 0.02550 -0.0864 0.9090 0.0355
-5.250 -0.1347 0.02785 0.02203 -0.0871 0.9004 0.0357
-5.000 -0.1114 0.02550 0.01928 -0.0869 0.8895 0.0359
-4.750 -0.0855 0.02384 0.01716 -0.0867 0.8793 0.0367
-4.500 -0.0603 0.02190 0.01498 -0.0867 0.8694 0.0374
-4.250 -0.0353 0.02057 0.01341 -0.0863 0.8581 0.0378
-4.000 -0.0093 0.01940 0.01201 -0.0860 0.8471 0.0380
-3.750 0.0173 0.01840 0.01078 -0.0856 0.8355 0.0384
-3.500 0.0436 0.01754 0.00974 -0.0851 0.8228 0.0388
-3.250 0.0696 0.01680 0.00883 -0.0846 0.8095 0.0394
-3.000 0.0958 0.01612 0.00801 -0.0841 0.7960 0.0399
-2.750 0.1220 0.01561 0.00738 -0.0836 0.7814 0.0410
-2.500 0.1482 0.01514 0.00678 -0.0830 0.7660 0.0424
-2.250 0.1742 0.01464 0.00616 -0.0824 0.7498 0.0431
-2.000 0.2000 0.01418 0.00559 -0.0818 0.7332 0.0437
-1.750 0.2256 0.01379 0.00510 -0.0811 0.7159 0.0443
-1.500 0.2510 0.01348 0.00467 -0.0804 0.6974 0.0450
-1.250 0.2758 0.01314 0.00423 -0.0796 0.6788 0.0459
-1.000 0.3004 0.01285 0.00387 -0.0789 0.6617 0.0473
-0.750 0.3257 0.01269 0.00363 -0.0782 0.6477 0.0494
-0.500 0.3514 0.01258 0.00345 -0.0777 0.6360 0.0524
-0.250 0.3774 0.01249 0.00328 -0.0772 0.6256 0.0550
0.000 0.4032 0.01238 0.00310 -0.0767 0.6163 0.0586
0.250 0.4293 0.01229 0.00299 -0.0762 0.6072 0.0652
0.500 0.4551 0.01216 0.00291 -0.0757 0.5992 0.0907
0.750 0.4747 0.01111 0.00299 -0.0747 0.5912 0.4509
1.250 0.5697 0.01011 0.00310 -0.0824 0.5744 1.0000
1.500 0.5944 0.01025 0.00314 -0.0817 0.5673 1.0000
1.750 0.6190 0.01038 0.00321 -0.0810 0.5594 1.0000
2.000 0.6437 0.01054 0.00328 -0.0802 0.5524 1.0000
2.250 0.6686 0.01067 0.00337 -0.0796 0.5451 1.0000
2.500 0.6934 0.01084 0.00346 -0.0789 0.5384 1.0000
2.750 0.7183 0.01097 0.00359 -0.0782 0.5305 1.0000
3.000 0.7429 0.01114 0.00370 -0.0775 0.5226 1.0000
3.250 0.7677 0.01128 0.00384 -0.0769 0.5137 1.0000
3.500 0.7922 0.01145 0.00397 -0.0761 0.5050 1.0000
3.750 0.8167 0.01160 0.00412 -0.0754 0.4946 1.0000
4.000 0.8411 0.01176 0.00427 -0.0747 0.4845 1.0000
4.250 0.8652 0.01195 0.00443 -0.0739 0.4742 1.0000
4.500 0.8895 0.01211 0.00460 -0.0732 0.4625 1.0000
4.750 0.9133 0.01229 0.00478 -0.0724 0.4491 1.0000
5.000 0.9366 0.01249 0.00496 -0.0715 0.4336 1.0000
5.250 0.9591 0.01272 0.00514 -0.0705 0.4150 1.0000
5.500 0.9815 0.01298 0.00535 -0.0694 0.3953 1.0000
5.750 1.0034 0.01328 0.00559 -0.0684 0.3752 1.0000
6.000 1.0249 0.01362 0.00587 -0.0673 0.3566 1.0000
6.250 1.0467 0.01396 0.00619 -0.0662 0.3409 1.0000
6.500 1.0681 0.01434 0.00653 -0.0651 0.3248 1.0000
6.750 1.0884 0.01477 0.00692 -0.0639 0.3051 1.0000
7.000 1.1087 0.01520 0.00732 -0.0627 0.2838 1.0000
7.250 1.1280 0.01570 0.00775 -0.0614 0.2601 1.0000
7.500 1.1449 0.01634 0.00825 -0.0597 0.2236 1.0000
7.750 1.1582 0.01723 0.00892 -0.0576 0.1820 1.0000
8.000 1.1697 0.01826 0.00973 -0.0553 0.1447 1.0000
8.250 1.1750 0.01969 0.01077 -0.0522 0.0832 1.0000
8.500 1.1839 0.02080 0.01174 -0.0496 0.0649 1.0000
8.750 1.1940 0.02167 0.01261 -0.0469 0.0583 1.0000
9.000 1.2053 0.02242 0.01344 -0.0445 0.0547 1.0000
9.250 1.2146 0.02331 0.01439 -0.0420 0.0516 1.0000
9.500 1.2209 0.02439 0.01552 -0.0392 0.0488 1.0000
9.750 1.2311 0.02527 0.01651 -0.0370 0.0470 1.0000
10.000 1.2398 0.02628 0.01762 -0.0349 0.0452 1.0000
10.250 1.2471 0.02742 0.01885 -0.0327 0.0433 1.0000
10.500 1.2523 0.02876 0.02028 -0.0306 0.0416 1.0000
10.750 1.2537 0.03045 0.02203 -0.0285 0.0401 1.0000
11.000 1.2566 0.03214 0.02381 -0.0267 0.0390 1.0000
11.250 1.2638 0.03359 0.02538 -0.0253 0.0375 1.0000
11.500 1.2687 0.03530 0.02719 -0.0240 0.0362 1.0000
11.750 1.2729 0.03714 0.02912 -0.0229 0.0349 1.0000
12.000 1.2763 0.03914 0.03120 -0.0220 0.0337 1.0000
12.250 1.2774 0.04145 0.03358 -0.0211 0.0326 1.0000
12.500 1.2768 0.04401 0.03618 -0.0203 0.0316 1.0000
12.750 1.2822 0.04606 0.03839 -0.0198 0.0305 1.0000
13.000 1.2860 0.04833 0.04078 -0.0194 0.0294 1.0000
13.250 1.2892 0.05072 0.04328 -0.0191 0.0284 1.0000
13.500 1.2919 0.05321 0.04585 -0.0190 0.0273 1.0000
13.750 1.2937 0.05584 0.04855 -0.0190 0.0266 1.0000
14.000 1.2943 0.05867 0.05142 -0.0191 0.0257 1.0000
14.250 1.2963 0.06138 0.05426 -0.0190 0.0250 1.0000
14.500 1.2987 0.06416 0.05722 -0.0192 0.0240 1.0000
14.750 1.3004 0.06705 0.06024 -0.0195 0.0232 1.0000
15.000 1.3016 0.07007 0.06338 -0.0199 0.0224 1.0000
15.250 1.3021 0.07324 0.06665 -0.0205 0.0218 1.0000
15.500 1.3020 0.07655 0.07004 -0.0213 0.0212 1.0000
15.750 1.3012 0.08003 0.07360 -0.0223 0.0207 1.0000
16.000 1.3003 0.08356 0.07722 -0.0231 0.0202 1.0000
16.250 1.2984 0.08739 0.08127 -0.0242 0.0196 1.0000
16.500 1.2953 0.09154 0.08561 -0.0256 0.0188 1.0000
16.750 1.2925 0.09566 0.08989 -0.0269 0.0184 1.0000
17.000 1.2887 0.10006 0.09443 -0.0287 0.0180 1.0000
17.250 1.2845 0.10459 0.09911 -0.0306 0.0176 1.0000
17.500 1.2800 0.10926 0.10391 -0.0327 0.0173 1.0000
17.750 1.2753 0.11406 0.10882 -0.0350 0.0170 1.0000
18.000 1.2707 0.11890 0.11377 -0.0374 0.0167 1.0000
18.250 1.2663 0.12376 0.11873 -0.0399 0.0165 1.0000
18.500 1.2614 0.12874 0.12381 -0.0425 0.0163 1.0000
18.750 1.2519 0.13487 0.13010 -0.0459 0.0160 1.0000
19.000 1.2389 0.14203 0.13748 -0.0500 0.0159 1.0000
19.250 1.2237 0.14994 0.14561 -0.0549 0.0157 1.0000
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