GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.09 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe425-il-1000000.txt Download as CSV file: xf-goe425-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2557 0.08221 0.07950 -0.0566 0.6912 0.0290
-10.750 -0.2537 0.07881 0.07609 -0.0576 0.6865 0.0292
-10.500 -0.2516 0.07542 0.07270 -0.0587 0.6814 0.0293
-10.250 -0.5258 0.04317 0.03980 -0.0889 0.7036 0.0292
-10.000 -0.5103 0.04189 0.03849 -0.0890 0.6973 0.0294
-9.750 -0.5199 0.03630 0.03246 -0.0892 0.6921 0.0278
-9.500 -0.5159 0.03244 0.02833 -0.0890 0.6873 0.0273
-9.250 -0.5080 0.02893 0.02447 -0.0884 0.6817 0.0271
-9.000 -0.4934 0.02649 0.02171 -0.0877 0.6758 0.0272
-8.750 -0.4751 0.02457 0.01953 -0.0871 0.6703 0.0273
-8.500 -0.4539 0.02323 0.01797 -0.0866 0.6642 0.0277
-8.250 -0.4316 0.02208 0.01660 -0.0862 0.6580 0.0279
-8.000 -0.4085 0.02089 0.01524 -0.0858 0.6524 0.0281
-7.750 -0.3843 0.01993 0.01412 -0.0854 0.6461 0.0282
-7.500 -0.3595 0.01919 0.01321 -0.0851 0.6395 0.0283
-7.250 -0.3335 0.01874 0.01264 -0.0848 0.6335 0.0285
-7.000 -0.3094 0.01738 0.01111 -0.0845 0.6267 0.0287
-6.750 -0.2848 0.01605 0.00968 -0.0842 0.6200 0.0290
-6.500 -0.2588 0.01525 0.00884 -0.0840 0.6130 0.0293
-6.250 -0.2325 0.01478 0.00831 -0.0838 0.6058 0.0297
-6.000 -0.2055 0.01439 0.00789 -0.0837 0.5994 0.0301
-5.750 -0.1787 0.01398 0.00744 -0.0836 0.5927 0.0305
-5.500 -0.1520 0.01356 0.00696 -0.0834 0.5864 0.0308
-5.250 -0.1250 0.01314 0.00650 -0.0832 0.5807 0.0311
-5.000 -0.0981 0.01276 0.00607 -0.0830 0.5747 0.0313
-4.750 -0.0713 0.01242 0.00568 -0.0828 0.5692 0.0316
-4.500 -0.0441 0.01208 0.00531 -0.0827 0.5643 0.0320
-4.250 -0.0170 0.01178 0.00497 -0.0825 0.5594 0.0323
-4.000 0.0100 0.01155 0.00468 -0.0823 0.5546 0.0326
-3.750 0.0376 0.01131 0.00443 -0.0822 0.5509 0.0329
-3.500 0.0655 0.01113 0.00422 -0.0822 0.5468 0.0332
-3.250 0.0912 0.01063 0.00369 -0.0818 0.5428 0.0340
-3.000 0.1182 0.01042 0.00345 -0.0817 0.5388 0.0347
-2.750 0.1459 0.01024 0.00326 -0.0816 0.5355 0.0353
-2.500 0.1740 0.01007 0.00308 -0.0816 0.5325 0.0360
-2.250 0.2021 0.00993 0.00292 -0.0816 0.5292 0.0367
-2.000 0.2300 0.00982 0.00278 -0.0816 0.5258 0.0374
-1.750 0.2580 0.00974 0.00267 -0.0816 0.5224 0.0381
-1.500 0.2859 0.00964 0.00253 -0.0815 0.5191 0.0390
-1.250 0.3141 0.00948 0.00238 -0.0816 0.5166 0.0407
-1.000 0.3426 0.00938 0.00229 -0.0817 0.5139 0.0425
-0.750 0.3710 0.00933 0.00223 -0.0817 0.5108 0.0444
-0.500 0.3991 0.00925 0.00214 -0.0817 0.5078 0.0494
-0.250 0.4261 0.00907 0.00210 -0.0816 0.5043 0.1058
0.000 0.4544 0.00898 0.00208 -0.0817 0.5019 0.1281
0.250 0.4802 0.00843 0.00201 -0.0816 0.4997 0.2857
0.500 0.5060 0.00798 0.00202 -0.0815 0.4972 0.4383
0.750 0.5339 0.00790 0.00207 -0.0815 0.4947 0.4885
1.000 0.5619 0.00788 0.00211 -0.0816 0.4921 0.5202
1.250 0.5897 0.00789 0.00217 -0.0816 0.4891 0.5463
1.500 0.6176 0.00793 0.00224 -0.0816 0.4860 0.5685
1.750 0.6460 0.00788 0.00228 -0.0817 0.4841 0.5961
2.000 0.6739 0.00783 0.00234 -0.0818 0.4819 0.6284
2.250 0.7013 0.00774 0.00240 -0.0817 0.4795 0.6743
2.500 0.7277 0.00763 0.00246 -0.0814 0.4770 0.7305
2.750 0.7501 0.00735 0.00255 -0.0802 0.4743 0.8540
3.000 0.8051 0.00736 0.00273 -0.0859 0.4698 0.9841
3.250 0.8495 0.00740 0.00278 -0.0896 0.4670 0.9975
3.500 0.8832 0.00746 0.00283 -0.0910 0.4640 1.0000
3.750 0.9095 0.00753 0.00288 -0.0907 0.4608 1.0000
4.000 0.9353 0.00762 0.00295 -0.0903 0.4576 1.0000
4.250 0.9607 0.00776 0.00305 -0.0899 0.4542 1.0000
4.500 0.9871 0.00783 0.00313 -0.0896 0.4517 1.0000
4.750 1.0136 0.00789 0.00320 -0.0894 0.4485 1.0000
5.000 1.0397 0.00796 0.00328 -0.0891 0.4447 1.0000
5.250 1.0652 0.00808 0.00337 -0.0887 0.4404 1.0000
5.500 1.0908 0.00820 0.00348 -0.0884 0.4362 1.0000
5.750 1.1175 0.00826 0.00356 -0.0882 0.4323 1.0000
6.000 1.1435 0.00836 0.00366 -0.0880 0.4274 1.0000
6.250 1.1687 0.00851 0.00379 -0.0876 0.4228 1.0000
6.500 1.1951 0.00861 0.00390 -0.0874 0.4186 1.0000
6.750 1.2213 0.00871 0.00402 -0.0872 0.4138 1.0000
7.000 1.2466 0.00887 0.00416 -0.0869 0.4083 1.0000
7.250 1.2724 0.00900 0.00430 -0.0867 0.4024 1.0000
7.500 1.2980 0.00915 0.00445 -0.0864 0.3959 1.0000
7.750 1.3226 0.00935 0.00463 -0.0860 0.3899 1.0000
8.000 1.3484 0.00949 0.00479 -0.0858 0.3829 1.0000
8.250 1.3721 0.00973 0.00500 -0.0853 0.3752 1.0000
8.500 1.3972 0.00991 0.00519 -0.0850 0.3673 1.0000
8.750 1.4201 0.01020 0.00545 -0.0844 0.3562 1.0000
9.000 1.4419 0.01054 0.00574 -0.0836 0.3436 1.0000
9.250 1.4639 0.01087 0.00603 -0.0829 0.3313 1.0000
9.500 1.4852 0.01123 0.00637 -0.0820 0.3185 1.0000
9.750 1.5050 0.01166 0.00674 -0.0810 0.3045 1.0000
10.000 1.5228 0.01217 0.00719 -0.0796 0.2880 1.0000
10.250 1.5367 0.01285 0.00776 -0.0777 0.2666 1.0000
10.500 1.5415 0.01379 0.00854 -0.0743 0.2356 1.0000
10.750 1.5346 0.01535 0.00985 -0.0696 0.1938 1.0000
11.000 1.5319 0.01688 0.01124 -0.0660 0.1693 1.0000
11.250 1.5370 0.01815 0.01247 -0.0638 0.1571 1.0000
11.500 1.5449 0.01938 0.01370 -0.0622 0.1483 1.0000
11.750 1.5501 0.02090 0.01521 -0.0606 0.1394 1.0000
12.000 1.5588 0.02230 0.01662 -0.0595 0.1314 1.0000
12.250 1.5635 0.02411 0.01842 -0.0584 0.1225 1.0000
12.500 1.5656 0.02623 0.02052 -0.0573 0.1121 1.0000
12.750 1.5667 0.02850 0.02277 -0.0563 0.1019 1.0000
13.000 1.5668 0.03090 0.02516 -0.0554 0.0937 1.0000
13.250 1.5659 0.03340 0.02768 -0.0544 0.0877 1.0000
13.500 1.5668 0.03576 0.03007 -0.0536 0.0837 1.0000
13.750 1.5648 0.03841 0.03274 -0.0527 0.0798 1.0000
14.000 1.5657 0.04079 0.03517 -0.0520 0.0769 1.0000
14.250 1.5662 0.04328 0.03770 -0.0513 0.0741 1.0000
14.500 1.5640 0.04610 0.04056 -0.0507 0.0712 1.0000
14.750 1.5622 0.04892 0.04343 -0.0502 0.0681 1.0000
15.000 1.5640 0.05144 0.04600 -0.0498 0.0655 1.0000
15.250 1.5614 0.05448 0.04907 -0.0494 0.0621 1.0000
15.500 1.5593 0.05747 0.05209 -0.0491 0.0586 1.0000
15.750 1.5576 0.06044 0.05509 -0.0488 0.0542 1.0000
16.000 1.5529 0.06382 0.05848 -0.0486 0.0492 1.0000
16.250 1.5449 0.06761 0.06226 -0.0484 0.0425 1.0000
16.500 1.5335 0.07178 0.06641 -0.0483 0.0345 1.0000
16.750 1.5219 0.07607 0.07068 -0.0483 0.0276 1.0000
17.000 1.5124 0.08022 0.07483 -0.0484 0.0234 1.0000
17.250 1.5054 0.08405 0.07869 -0.0485 0.0208 1.0000
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