GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 200,000 Max Cl/Cd: 66.66 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe530-il-200000-n5.txt Download as CSV file: xf-goe530-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2588 0.11879 0.11491 -0.0426 1.0000 0.0467
-11.250 -0.2628 0.11586 0.11202 -0.0433 1.0000 0.0468
-11.000 -0.2648 0.11330 0.10951 -0.0431 1.0000 0.0468
-10.500 -0.2429 0.10473 0.10094 -0.0474 0.9875 0.0424
-10.250 -0.2355 0.09989 0.09608 -0.0521 0.9798 0.0418
-10.000 -0.2279 0.09507 0.09125 -0.0569 0.9717 0.0419
-9.750 -0.2124 0.09143 0.08760 -0.0602 0.9650 0.0417
-9.500 -0.1973 0.08745 0.08361 -0.0644 0.9582 0.0416
-9.250 -0.1834 0.08282 0.07895 -0.0698 0.9514 0.0415
-9.000 -0.1713 0.07784 0.07395 -0.0758 0.9426 0.0415
-8.750 -0.1519 0.07441 0.07050 -0.0808 0.9347 0.0428
-8.500 -0.1395 0.06956 0.06561 -0.0875 0.9234 0.0429
-8.250 -0.1345 0.06495 0.06094 -0.0928 0.9091 0.0430
-8.000 -0.1368 0.06065 0.05655 -0.0957 0.8945 0.0430
-7.750 -0.1409 0.05591 0.05169 -0.0980 0.8814 0.0430
-7.500 -0.1415 0.05208 0.04773 -0.0985 0.8691 0.0432
-7.250 -0.1413 0.04843 0.04392 -0.0983 0.8572 0.0436
-7.000 -0.1377 0.04477 0.04006 -0.0978 0.8469 0.0443
-6.750 -0.1411 0.03983 0.03481 -0.0962 0.8353 0.0453
-6.500 -0.1754 0.02860 0.02230 -0.0904 0.8245 0.0469
-6.250 -0.1559 0.02774 0.02134 -0.0891 0.8149 0.0473
-6.000 -0.1356 0.02710 0.02061 -0.0878 0.8046 0.0479
-5.750 -0.1144 0.02639 0.01977 -0.0866 0.7949 0.0486
-5.500 -0.0961 0.02520 0.01836 -0.0849 0.7849 0.0496
-5.250 -0.0785 0.02343 0.01619 -0.0831 0.7768 0.0510
-5.000 -0.0611 0.02144 0.01363 -0.0810 0.7692 0.0524
-4.750 -0.0374 0.02087 0.01300 -0.0802 0.7614 0.0530
-4.500 -0.0129 0.02039 0.01242 -0.0794 0.7545 0.0538
-4.250 0.0109 0.01993 0.01189 -0.0784 0.7465 0.0550
-4.000 0.0355 0.01930 0.01105 -0.0776 0.7393 0.0565
-3.750 0.0598 0.01851 0.00997 -0.0766 0.7319 0.0583
-3.500 0.0849 0.01800 0.00941 -0.0759 0.7242 0.0592
-3.250 0.1110 0.01762 0.00896 -0.0753 0.7176 0.0602
-3.000 0.1359 0.01728 0.00857 -0.0745 0.7094 0.0618
-2.750 0.1619 0.01692 0.00806 -0.0739 0.7018 0.0638
-2.500 0.1877 0.01652 0.00754 -0.0732 0.6941 0.0655
-2.250 0.2133 0.01615 0.00719 -0.0726 0.6860 0.0667
-2.000 0.2393 0.01589 0.00688 -0.0720 0.6784 0.0685
-1.750 0.2646 0.01564 0.00659 -0.0712 0.6693 0.0707
-1.500 0.2909 0.01542 0.00624 -0.0706 0.6613 0.0727
-1.250 0.3156 0.01508 0.00596 -0.0698 0.6518 0.0743
-1.000 0.3409 0.01487 0.00573 -0.0691 0.6429 0.0764
-0.750 0.3653 0.01469 0.00555 -0.0682 0.6324 0.0790
-0.500 0.3902 0.01455 0.00532 -0.0673 0.6224 0.0812
-0.250 0.4136 0.01431 0.00512 -0.0662 0.6103 0.0833
0.000 0.4370 0.01417 0.00497 -0.0651 0.5971 0.0861
0.250 0.4601 0.01408 0.00483 -0.0640 0.5831 0.0894
0.500 0.4828 0.01401 0.00469 -0.0627 0.5684 0.0921
0.750 0.5051 0.01391 0.00459 -0.0614 0.5535 0.0955
1.000 0.5277 0.01388 0.00453 -0.0602 0.5392 0.1002
1.250 0.5499 0.01387 0.00447 -0.0589 0.5248 0.1054
1.500 0.5716 0.01387 0.00445 -0.0575 0.5108 0.1125
2.000 0.6138 0.01383 0.00452 -0.0546 0.4842 0.1685
2.250 0.6320 0.01358 0.00461 -0.0527 0.4725 0.3013
2.750 0.8625 0.01341 0.00563 -0.0896 0.4320 1.0000
3.000 0.8828 0.01366 0.00577 -0.0881 0.4228 1.0000
3.250 0.9036 0.01387 0.00593 -0.0867 0.4133 1.0000
3.500 0.9233 0.01414 0.00610 -0.0851 0.4047 1.0000
3.750 0.9441 0.01434 0.00628 -0.0837 0.3962 1.0000
4.000 0.9635 0.01461 0.00647 -0.0820 0.3884 1.0000
4.250 0.9838 0.01483 0.00667 -0.0805 0.3807 1.0000
4.500 1.0029 0.01509 0.00689 -0.0789 0.3728 1.0000
4.750 1.0219 0.01535 0.00712 -0.0772 0.3653 1.0000
5.000 1.0405 0.01561 0.00735 -0.0754 0.3570 1.0000
5.250 1.0580 0.01591 0.00761 -0.0735 0.3496 1.0000
5.500 1.0762 0.01617 0.00787 -0.0716 0.3414 1.0000
5.750 1.0920 0.01650 0.00814 -0.0694 0.3340 1.0000
6.000 1.1097 0.01677 0.00843 -0.0675 0.3266 1.0000
6.250 1.1251 0.01709 0.00872 -0.0653 0.3197 1.0000
6.500 1.1401 0.01742 0.00903 -0.0629 0.3125 1.0000
6.750 1.1541 0.01775 0.00935 -0.0604 0.3046 1.0000
7.000 1.1663 0.01813 0.00969 -0.0576 0.2974 1.0000
7.250 1.1775 0.01845 0.01002 -0.0546 0.2898 1.0000
7.500 1.1852 0.01883 0.01035 -0.0510 0.2839 1.0000
7.750 1.1964 0.01917 0.01071 -0.0481 0.2782 1.0000
8.000 1.2069 0.01955 0.01111 -0.0452 0.2724 1.0000
8.250 1.2156 0.02003 0.01154 -0.0420 0.2671 1.0000
8.500 1.2284 0.02043 0.01198 -0.0396 0.2625 1.0000
8.750 1.2400 0.02089 0.01246 -0.0371 0.2570 1.0000
9.000 1.2501 0.02144 0.01300 -0.0345 0.2521 1.0000
9.250 1.2617 0.02197 0.01355 -0.0322 0.2475 1.0000
9.500 1.2743 0.02249 0.01411 -0.0301 0.2427 1.0000
9.750 1.2857 0.02309 0.01473 -0.0280 0.2384 1.0000
10.000 1.2962 0.02376 0.01540 -0.0258 0.2347 1.0000
10.250 1.3089 0.02437 0.01606 -0.0239 0.2308 1.0000
10.500 1.3216 0.02499 0.01676 -0.0221 0.2268 1.0000
10.750 1.3324 0.02572 0.01752 -0.0203 0.2226 1.0000
11.000 1.3419 0.02656 0.01836 -0.0183 0.2187 1.0000
11.250 1.3534 0.02732 0.01920 -0.0167 0.2144 1.0000
11.500 1.3639 0.02815 0.02010 -0.0150 0.2093 1.0000
11.750 1.3718 0.02917 0.02113 -0.0132 0.2042 1.0000
12.000 1.3811 0.03015 0.02217 -0.0116 0.2001 1.0000
12.250 1.3914 0.03111 0.02323 -0.0102 0.1950 1.0000
12.500 1.3986 0.03229 0.02446 -0.0087 0.1898 1.0000
12.750 1.4055 0.03354 0.02577 -0.0073 0.1838 1.0000
13.000 1.4114 0.03492 0.02721 -0.0059 0.1759 1.0000
13.250 1.4164 0.03643 0.02878 -0.0047 0.1689 1.0000
13.500 1.4200 0.03811 0.03051 -0.0035 0.1604 1.0000
13.750 1.4217 0.04001 0.03245 -0.0023 0.1491 1.0000
14.000 1.4194 0.04236 0.03480 -0.0013 0.1353 1.0000
14.250 1.4111 0.04540 0.03779 -0.0003 0.1185 1.0000
14.500 1.3996 0.04893 0.04126 0.0005 0.1051 1.0000
14.750 1.3881 0.05264 0.04496 0.0010 0.0973 1.0000
15.000 1.3788 0.05628 0.04864 0.0012 0.0928 1.0000
15.250 1.3687 0.06016 0.05257 0.0012 0.0894 1.0000
15.500 1.3604 0.06397 0.05647 0.0010 0.0867 1.0000
15.750 1.3514 0.06799 0.06058 0.0007 0.0846 1.0000
16.000 1.3401 0.07241 0.06508 0.0000 0.0827 1.0000
16.250 1.3276 0.07710 0.06984 -0.0008 0.0810 1.0000
16.500 1.3201 0.08122 0.07406 -0.0015 0.0794 1.0000
16.750 1.3136 0.08524 0.07819 -0.0023 0.0779 1.0000
17.000 1.3064 0.08939 0.08243 -0.0032 0.0765 1.0000
17.250 1.2989 0.09361 0.08673 -0.0042 0.0750 1.0000
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