GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 200,000 Max Cl/Cd: 60.43 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe383-il-200000-n5.txt Download as CSV file: xf-goe383-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5021 0.05702 0.05180 -0.1065 0.9032 0.0391
-12.750 -0.5369 0.05050 0.04491 -0.1105 0.8847 0.0390
-12.500 -0.5548 0.04666 0.04078 -0.1113 0.8666 0.0391
-12.250 -0.5657 0.04381 0.03768 -0.1110 0.8490 0.0391
-12.000 -0.5717 0.04153 0.03515 -0.1098 0.8323 0.0392
-11.750 -0.5741 0.03961 0.03299 -0.1081 0.8169 0.0394
-11.500 -0.5746 0.03802 0.03116 -0.1059 0.8023 0.0395
-11.250 -0.5703 0.03657 0.02949 -0.1040 0.7889 0.0397
-11.000 -0.5619 0.03517 0.02785 -0.1024 0.7777 0.0399
-10.750 -0.5506 0.03384 0.02631 -0.1010 0.7664 0.0401
-10.500 -0.5374 0.03261 0.02484 -0.0997 0.7570 0.0404
-10.250 -0.5220 0.03143 0.02347 -0.0986 0.7475 0.0407
-10.000 -0.5055 0.03036 0.02218 -0.0975 0.7391 0.0410
-9.750 -0.4877 0.02936 0.02096 -0.0965 0.7317 0.0415
-9.500 -0.4688 0.02842 0.01980 -0.0956 0.7240 0.0419
-9.250 -0.4486 0.02756 0.01873 -0.0947 0.7171 0.0423
-9.000 -0.4259 0.02676 0.01788 -0.0942 0.7109 0.0426
-8.750 -0.4029 0.02603 0.01711 -0.0938 0.7048 0.0430
-8.500 -0.3797 0.02534 0.01635 -0.0933 0.6994 0.0434
-8.250 -0.3563 0.02469 0.01561 -0.0927 0.6947 0.0437
-8.000 -0.3325 0.02406 0.01491 -0.0922 0.6901 0.0442
-7.750 -0.3084 0.02345 0.01424 -0.0918 0.6848 0.0446
-7.500 -0.2843 0.02287 0.01358 -0.0913 0.6791 0.0452
-7.250 -0.2602 0.02234 0.01294 -0.0907 0.6735 0.0457
-7.000 -0.2358 0.02184 0.01234 -0.0902 0.6679 0.0462
-6.750 -0.2112 0.02136 0.01180 -0.0897 0.6616 0.0468
-6.500 -0.1873 0.02083 0.01128 -0.0891 0.6562 0.0473
-6.250 -0.1630 0.02039 0.01082 -0.0886 0.6520 0.0481
-5.750 -0.1133 0.01964 0.01000 -0.0878 0.6442 0.0501
-5.500 -0.0881 0.01930 0.00963 -0.0873 0.6402 0.0512
-5.250 -0.0634 0.01891 0.00924 -0.0868 0.6362 0.0522
-5.000 -0.0387 0.01856 0.00887 -0.0864 0.6323 0.0532
-4.750 -0.0135 0.01826 0.00852 -0.0859 0.6285 0.0544
-4.500 0.0122 0.01800 0.00820 -0.0855 0.6249 0.0559
-4.250 0.0375 0.01771 0.00792 -0.0851 0.6210 0.0574
-4.000 0.0630 0.01743 0.00765 -0.0848 0.6171 0.0594
-3.750 0.0890 0.01720 0.00740 -0.0844 0.6132 0.0623
-3.500 0.1147 0.01693 0.00713 -0.0840 0.6093 0.0659
-3.250 0.1407 0.01670 0.00688 -0.0837 0.6055 0.0715
-3.000 0.1663 0.01643 0.00670 -0.0834 0.6016 0.0838
-2.750 0.1914 0.01613 0.00659 -0.0830 0.5972 0.1170
-2.500 0.2170 0.01589 0.00647 -0.0826 0.5928 0.1478
-2.250 0.2426 0.01564 0.00635 -0.0823 0.5887 0.1783
-2.000 0.2677 0.01535 0.00625 -0.0820 0.5848 0.2280
-1.750 0.2937 0.01517 0.00618 -0.0817 0.5811 0.2771
-1.250 0.3436 0.01476 0.00615 -0.0808 0.5713 0.3629
-1.000 0.3676 0.01447 0.00611 -0.0801 0.5664 0.4268
-0.750 0.3913 0.01420 0.00608 -0.0794 0.5620 0.5071
-0.500 0.4138 0.01396 0.00621 -0.0782 0.5574 0.5950
-0.250 0.4375 0.01386 0.00634 -0.0772 0.5520 0.6621
0.000 0.4626 0.01384 0.00640 -0.0764 0.5468 0.7028
0.250 0.4884 0.01383 0.00642 -0.0757 0.5422 0.7343
0.500 0.5137 0.01385 0.00650 -0.0750 0.5368 0.7615
0.750 0.5387 0.01388 0.00659 -0.0743 0.5304 0.7875
1.000 0.5639 0.01391 0.00664 -0.0735 0.5246 0.8140
1.250 0.5894 0.01398 0.00672 -0.0727 0.5191 0.8400
1.500 0.6153 0.01407 0.00686 -0.0721 0.5127 0.8638
1.750 0.6424 0.01418 0.00694 -0.0717 0.5068 0.8853
2.000 0.6718 0.01430 0.00703 -0.0719 0.5012 0.9029
2.250 0.7027 0.01446 0.00718 -0.0725 0.4942 0.9208
2.500 0.7358 0.01462 0.00727 -0.0736 0.4878 0.9378
2.750 0.7707 0.01481 0.00741 -0.0751 0.4819 0.9530
3.000 0.8064 0.01501 0.00757 -0.0768 0.4755 0.9668
3.250 0.8436 0.01522 0.00770 -0.0789 0.4695 0.9794
3.500 0.8855 0.01545 0.00788 -0.0821 0.4635 0.9886
3.750 0.9266 0.01569 0.00807 -0.0852 0.4573 0.9967
4.000 0.9512 0.01588 0.00817 -0.0850 0.4517 1.0000
4.250 0.9644 0.01606 0.00830 -0.0825 0.4461 1.0000
4.500 0.9777 0.01625 0.00845 -0.0801 0.4398 1.0000
4.750 0.9917 0.01648 0.00859 -0.0777 0.4340 1.0000
5.000 1.0074 0.01672 0.00877 -0.0757 0.4290 1.0000
5.250 1.0240 0.01696 0.00901 -0.0739 0.4243 1.0000
5.500 1.0412 0.01723 0.00925 -0.0722 0.4198 1.0000
5.750 1.0588 0.01752 0.00948 -0.0706 0.4157 1.0000
6.000 1.0765 0.01782 0.00973 -0.0690 0.4118 1.0000
6.250 1.0926 0.01813 0.01007 -0.0673 0.4076 1.0000
6.500 1.1096 0.01846 0.01041 -0.0657 0.4033 1.0000
6.750 1.1273 0.01883 0.01075 -0.0643 0.3993 1.0000
7.000 1.1463 0.01921 0.01108 -0.0632 0.3955 1.0000
7.250 1.1642 0.01962 0.01150 -0.0619 0.3916 1.0000
7.500 1.1807 0.02006 0.01199 -0.0606 0.3873 1.0000
7.750 1.1976 0.02052 0.01247 -0.0593 0.3829 1.0000
8.000 1.2153 0.02100 0.01291 -0.0582 0.3789 1.0000
8.250 1.2341 0.02148 0.01335 -0.0572 0.3753 1.0000
8.500 1.2492 0.02205 0.01402 -0.0559 0.3711 1.0000
8.750 1.2643 0.02265 0.01467 -0.0547 0.3666 1.0000
9.000 1.2796 0.02327 0.01529 -0.0535 0.3621 1.0000
9.250 1.2960 0.02388 0.01586 -0.0524 0.3580 1.0000
9.500 1.3091 0.02465 0.01673 -0.0511 0.3534 1.0000
9.750 1.3219 0.02546 0.01760 -0.0499 0.3485 1.0000
10.000 1.3351 0.02627 0.01842 -0.0488 0.3439 1.0000
10.250 1.3483 0.02711 0.01926 -0.0477 0.3394 1.0000
10.500 1.3583 0.02819 0.02044 -0.0464 0.3337 1.0000
10.750 1.3681 0.02929 0.02156 -0.0453 0.3280 1.0000
11.000 1.3780 0.03041 0.02267 -0.0441 0.3228 1.0000
11.250 1.3857 0.03178 0.02414 -0.0430 0.3165 1.0000
11.500 1.3932 0.03315 0.02553 -0.0419 0.3104 1.0000
11.750 1.4001 0.03463 0.02704 -0.0409 0.3044 1.0000
12.000 1.4055 0.03630 0.02877 -0.0400 0.2977 1.0000
12.250 1.4111 0.03794 0.03038 -0.0390 0.2919 1.0000
12.500 1.4169 0.03972 0.03225 -0.0382 0.2857 1.0000
12.750 1.4216 0.04159 0.03414 -0.0375 0.2799 1.0000
13.000 1.4266 0.04345 0.03602 -0.0367 0.2745 1.0000
13.250 1.4304 0.04552 0.03814 -0.0361 0.2684 1.0000
13.500 1.4329 0.04766 0.04027 -0.0354 0.2625 1.0000
13.750 1.4354 0.04994 0.04261 -0.0349 0.2562 1.0000
14.000 1.4359 0.05240 0.04506 -0.0343 0.2498 1.0000
14.250 1.4374 0.05480 0.04750 -0.0339 0.2439 1.0000
14.500 1.4378 0.05739 0.05013 -0.0335 0.2378 1.0000
14.750 1.4385 0.05990 0.05262 -0.0331 0.2324 1.0000
15.000 1.4395 0.06255 0.05535 -0.0329 0.2272 1.0000
15.250 1.4406 0.06514 0.05798 -0.0327 0.2224 1.0000
15.500 1.4425 0.06762 0.06044 -0.0324 0.2184 1.0000
15.750 1.4443 0.07028 0.06322 -0.0324 0.2143 1.0000
16.000 1.4449 0.07306 0.06606 -0.0324 0.2103 1.0000
16.250 1.4464 0.07569 0.06871 -0.0323 0.2064 1.0000
16.500 1.4471 0.07849 0.07157 -0.0324 0.2028 1.0000
16.750 1.4466 0.08152 0.07470 -0.0326 0.1988 1.0000
17.000 1.4454 0.08463 0.07787 -0.0328 0.1947 1.0000
17.250 1.4454 0.08753 0.08078 -0.0330 0.1907 1.0000
17.500 1.4411 0.09120 0.08459 -0.0335 0.1863 1.0000
17.750 1.4368 0.09481 0.08827 -0.0340 0.1815 1.0000
18.000 1.4342 0.09817 0.09166 -0.0346 0.1771 1.0000
18.250 1.4278 0.10223 0.09585 -0.0354 0.1720 1.0000
18.500 1.4219 0.10615 0.09982 -0.0362 0.1667 1.0000
18.750 1.4157 0.11019 0.10397 -0.0371 0.1614 1.0000
19.000 1.4068 0.11462 0.10845 -0.0382 0.1547 1.0000
19.250 1.3965 0.11935 0.11326 -0.0396 0.1465 1.0000
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