GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 200,000 Max Cl/Cd: 74.01 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe425-il-200000-n5.txt Download as CSV file: xf-goe425-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2941 0.10030 0.09592 -0.0485 0.7662 0.0379
-10.500 -0.3814 0.07098 0.06657 -0.0690 0.7707 0.0348
-10.250 -0.4063 0.06114 0.05656 -0.0785 0.7622 0.0346
-10.000 -0.4312 0.05359 0.04876 -0.0869 0.7524 0.0344
-9.750 -0.4498 0.04881 0.04364 -0.0890 0.7442 0.0344
-9.500 -0.4559 0.04466 0.03912 -0.0900 0.7361 0.0344
-9.000 -0.4476 0.03818 0.03178 -0.0900 0.7218 0.0346
-8.750 -0.4362 0.03572 0.02888 -0.0895 0.7147 0.0347
-8.500 -0.4208 0.03359 0.02643 -0.0891 0.7080 0.0350
-8.250 -0.4014 0.03192 0.02462 -0.0888 0.7006 0.0354
-8.000 -0.3804 0.03066 0.02321 -0.0885 0.6941 0.0358
-7.750 -0.3587 0.02941 0.02182 -0.0882 0.6873 0.0363
-7.500 -0.3370 0.02813 0.02031 -0.0878 0.6808 0.0367
-7.250 -0.3148 0.02686 0.01878 -0.0874 0.6753 0.0369
-7.000 -0.2914 0.02568 0.01740 -0.0871 0.6687 0.0372
-6.750 -0.2675 0.02463 0.01613 -0.0867 0.6626 0.0375
-6.500 -0.2430 0.02368 0.01498 -0.0863 0.6570 0.0378
-6.250 -0.2179 0.02280 0.01394 -0.0860 0.6503 0.0381
-6.000 -0.1926 0.02202 0.01298 -0.0856 0.6443 0.0385
-5.750 -0.1669 0.02131 0.01213 -0.0853 0.6388 0.0390
-5.500 -0.1407 0.02071 0.01140 -0.0851 0.6327 0.0396
-5.250 -0.1145 0.02022 0.01074 -0.0848 0.6274 0.0402
-5.000 -0.0887 0.01952 0.00999 -0.0845 0.6228 0.0407
-4.750 -0.0627 0.01886 0.00935 -0.0843 0.6171 0.0412
-4.500 -0.0369 0.01832 0.00878 -0.0840 0.6119 0.0417
-4.250 -0.0111 0.01785 0.00826 -0.0836 0.6073 0.0422
-4.000 0.0150 0.01742 0.00782 -0.0834 0.6020 0.0428
-3.750 0.0411 0.01703 0.00740 -0.0831 0.5971 0.0434
-3.500 0.0673 0.01668 0.00700 -0.0828 0.5930 0.0442
-3.250 0.0936 0.01638 0.00663 -0.0826 0.5893 0.0450
-3.000 0.1203 0.01612 0.00635 -0.0824 0.5846 0.0461
-2.750 0.1465 0.01581 0.00601 -0.0822 0.5801 0.0474
-2.500 0.1730 0.01555 0.00570 -0.0820 0.5762 0.0491
-2.250 0.1998 0.01537 0.00543 -0.0818 0.5728 0.0506
-2.000 0.2271 0.01520 0.00524 -0.0817 0.5689 0.0523
-1.750 0.2543 0.01505 0.00506 -0.0816 0.5650 0.0545
-1.500 0.2814 0.01488 0.00487 -0.0814 0.5612 0.0584
-1.000 0.3352 0.01451 0.00466 -0.0812 0.5547 0.1214
-0.750 0.3594 0.01383 0.00458 -0.0811 0.5512 0.2674
-0.500 0.3838 0.01339 0.00463 -0.0807 0.5476 0.4087
-0.250 0.4100 0.01329 0.00470 -0.0804 0.5441 0.4807
0.000 0.4369 0.01327 0.00473 -0.0802 0.5411 0.5249
0.250 0.4634 0.01325 0.00479 -0.0799 0.5382 0.5655
0.500 0.4892 0.01319 0.00491 -0.0794 0.5347 0.6110
0.750 0.5151 0.01313 0.00499 -0.0790 0.5311 0.6528
1.000 0.5412 0.01308 0.00505 -0.0785 0.5278 0.6881
1.250 0.5677 0.01305 0.00509 -0.0781 0.5247 0.7197
1.500 0.5944 0.01302 0.00513 -0.0777 0.5219 0.7619
1.750 0.6256 0.01291 0.00529 -0.0781 0.5184 0.8479
2.000 0.6826 0.01294 0.00542 -0.0841 0.5143 0.9626
2.250 0.7223 0.01308 0.00551 -0.0868 0.5108 1.0000
2.500 0.7479 0.01323 0.00558 -0.0865 0.5079 1.0000
2.750 0.7740 0.01340 0.00566 -0.0862 0.5052 1.0000
3.000 0.7993 0.01357 0.00581 -0.0858 0.5020 1.0000
3.250 0.8246 0.01373 0.00599 -0.0855 0.4985 1.0000
3.500 0.8502 0.01391 0.00615 -0.0851 0.4953 1.0000
3.750 0.8760 0.01408 0.00629 -0.0848 0.4923 1.0000
4.000 0.9022 0.01426 0.00642 -0.0846 0.4895 1.0000
4.250 0.9282 0.01446 0.00658 -0.0844 0.4866 1.0000
4.500 0.9531 0.01465 0.00683 -0.0840 0.4829 1.0000
4.750 0.9784 0.01485 0.00706 -0.0837 0.4794 1.0000
5.000 1.0039 0.01505 0.00726 -0.0834 0.4763 1.0000
5.250 1.0298 0.01524 0.00744 -0.0831 0.4734 1.0000
5.500 1.0559 0.01545 0.00761 -0.0829 0.4702 1.0000
5.750 1.0797 0.01566 0.00791 -0.0824 0.4655 1.0000
6.000 1.1041 0.01585 0.00815 -0.0819 0.4609 1.0000
6.250 1.1292 0.01602 0.00831 -0.0816 0.4568 1.0000
6.500 1.1546 0.01623 0.00851 -0.0813 0.4534 1.0000
6.750 1.1779 0.01648 0.00887 -0.0807 0.4488 1.0000
7.000 1.2017 0.01671 0.00916 -0.0802 0.4444 1.0000
7.250 1.2261 0.01692 0.00937 -0.0798 0.4404 1.0000
7.500 1.2498 0.01714 0.00964 -0.0792 0.4359 1.0000
7.750 1.2717 0.01739 0.00999 -0.0784 0.4295 1.0000
8.000 1.2944 0.01757 0.01017 -0.0777 0.4237 1.0000
8.250 1.3159 0.01784 0.01052 -0.0769 0.4175 1.0000
8.500 1.3373 0.01812 0.01087 -0.0761 0.4116 1.0000
8.750 1.3589 0.01836 0.01111 -0.0752 0.4062 1.0000
9.000 1.3779 0.01870 0.01157 -0.0741 0.3984 1.0000
9.250 1.3969 0.01900 0.01188 -0.0729 0.3912 1.0000
9.500 1.4143 0.01939 0.01237 -0.0715 0.3831 1.0000
9.750 1.4307 0.01978 0.01276 -0.0700 0.3758 1.0000
10.000 1.4447 0.02024 0.01332 -0.0681 0.3679 1.0000
10.250 1.4564 0.02077 0.01386 -0.0659 0.3595 1.0000
10.500 1.4679 0.02142 0.01458 -0.0640 0.3501 1.0000
10.750 1.4776 0.02217 0.01537 -0.0620 0.3411 1.0000
11.000 1.4860 0.02308 0.01631 -0.0600 0.3310 1.0000
11.250 1.4937 0.02413 0.01742 -0.0582 0.3207 1.0000
11.500 1.4981 0.02545 0.01877 -0.0563 0.3091 1.0000
11.750 1.4994 0.02712 0.02045 -0.0545 0.2952 1.0000
12.000 1.4980 0.02917 0.02249 -0.0529 0.2787 1.0000
12.250 1.4925 0.03171 0.02502 -0.0514 0.2587 1.0000
12.500 1.4805 0.03496 0.02819 -0.0499 0.2361 1.0000
12.750 1.4640 0.03878 0.03192 -0.0485 0.2118 1.0000
13.000 1.4451 0.04298 0.03602 -0.0472 0.1927 1.0000
13.250 1.4285 0.04708 0.04007 -0.0462 0.1793 1.0000
13.500 1.4156 0.05098 0.04396 -0.0455 0.1688 1.0000
13.750 1.4065 0.05463 0.04761 -0.0450 0.1602 1.0000
14.000 1.3971 0.05838 0.05136 -0.0446 0.1526 1.0000
14.250 1.3937 0.06156 0.05459 -0.0444 0.1454 1.0000
14.500 1.3883 0.06503 0.05807 -0.0442 0.1384 1.0000
14.750 1.3866 0.06811 0.06120 -0.0441 0.1320 1.0000
15.000 1.3841 0.07133 0.06447 -0.0440 0.1253 1.0000
15.250 1.3824 0.07450 0.06768 -0.0440 0.1192 1.0000
15.500 1.3805 0.07774 0.07095 -0.0442 0.1125 1.0000
15.750 1.3786 0.08099 0.07423 -0.0443 0.1066 1.0000
16.000 1.3765 0.08430 0.07758 -0.0445 0.1005 1.0000
16.250 1.3743 0.08768 0.08097 -0.0448 0.0954 1.0000
16.500 1.3729 0.09097 0.08430 -0.0452 0.0904 1.0000
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Polar data table (+)
Polar graphs
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