GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 50,000 Max Cl/Cd: 13.4 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe420-il-50000-n5.txt Download as CSV file: xf-goe420-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3088 0.13599 0.12847 -0.0479 1.0000 0.0847
-12.000 -0.3188 0.13341 0.12594 -0.0470 1.0000 0.0842
-11.750 -0.3294 0.13074 0.12334 -0.0462 1.0000 0.0841
-11.500 -0.3234 0.12578 0.11838 -0.0501 0.9956 0.0848
-11.250 -0.3190 0.12038 0.11296 -0.0544 0.9905 0.0855
-11.000 -0.3182 0.11456 0.10713 -0.0588 0.9851 0.0860
-10.750 -0.3192 0.10813 0.10069 -0.0637 0.9804 0.0861
-10.500 -0.3300 0.10063 0.09318 -0.0686 0.9742 0.0861
-10.250 -0.3642 0.08836 0.08088 -0.0768 0.9682 0.0859
-10.000 -0.4600 0.06946 0.06161 -0.0908 0.9565 0.0845
-9.750 -0.5060 0.06212 0.05393 -0.0959 0.9444 0.0841
-9.500 -0.5218 0.05822 0.04973 -0.0971 0.9348 0.0846
-9.250 -0.5320 0.05547 0.04674 -0.0961 0.9245 0.0852
-9.000 -0.5265 0.05251 0.04346 -0.0970 0.9175 0.0866
-8.750 -0.5280 0.05039 0.04103 -0.0954 0.9085 0.0880
-8.500 -0.5142 0.04867 0.03917 -0.0953 0.9017 0.0901
-8.250 -0.4882 0.04728 0.03774 -0.0967 0.8973 0.0929
-8.000 -0.4872 0.04624 0.03658 -0.0938 0.8878 0.0948
-7.750 -0.4696 0.04459 0.03462 -0.0938 0.8819 0.0982
-7.500 -0.4411 0.04342 0.03347 -0.0950 0.8781 0.1014
-7.250 -0.4403 0.04279 0.03278 -0.0915 0.8683 0.1038
-7.000 -0.4192 0.04160 0.03139 -0.0914 0.8627 0.1091
-6.750 -0.3909 0.04063 0.03044 -0.0924 0.8589 0.1155
-6.500 -0.3911 0.04011 0.02979 -0.0886 0.8492 0.1205
-6.250 -0.3698 0.03928 0.02900 -0.0884 0.8436 0.1286
-6.000 -0.3408 0.03825 0.02793 -0.0894 0.8397 0.1416
-5.750 -0.3402 0.03786 0.02753 -0.0857 0.8301 0.1507
-5.500 -0.3187 0.03704 0.02679 -0.0854 0.8243 0.1684
-5.250 -0.2878 0.03621 0.02604 -0.0865 0.8203 0.1944
-5.000 -0.2850 0.03616 0.02607 -0.0830 0.8101 0.2110
-4.750 -0.2582 0.03592 0.02591 -0.0831 0.8041 0.2388
-4.500 -0.2214 0.03567 0.02566 -0.0845 0.8002 0.2694
-4.250 -0.2193 0.03589 0.02585 -0.0808 0.7884 0.2853
-4.000 -0.1865 0.03575 0.02565 -0.0814 0.7833 0.3116
-3.750 -0.1734 0.03597 0.02585 -0.0791 0.7743 0.3309
-3.500 -0.1502 0.03603 0.02587 -0.0783 0.7672 0.3528
-3.250 -0.1154 0.03579 0.02555 -0.0790 0.7631 0.3745
-3.000 -0.1084 0.03606 0.02580 -0.0760 0.7527 0.3855
-2.750 -0.0789 0.03582 0.02542 -0.0761 0.7470 0.4018
-2.500 -0.0419 0.03541 0.02487 -0.0772 0.7435 0.4187
-2.250 -0.0382 0.03587 0.02537 -0.0738 0.7320 0.4273
-2.000 -0.0052 0.03556 0.02493 -0.0743 0.7272 0.4428
-1.750 0.0121 0.03571 0.02504 -0.0728 0.7190 0.4548
-1.500 0.0339 0.03572 0.02500 -0.0718 0.7114 0.4675
-1.250 0.0688 0.03534 0.02452 -0.0725 0.7074 0.4841
-1.000 0.0770 0.03586 0.02504 -0.0699 0.6966 0.4968
-0.750 0.1062 0.03566 0.02484 -0.0697 0.6911 0.5142
-0.500 0.1427 0.03520 0.02435 -0.0703 0.6878 0.5332
-0.250 0.1463 0.03603 0.02517 -0.0674 0.6755 0.5453
0.000 0.1798 0.03566 0.02475 -0.0678 0.6712 0.5620
0.500 0.2179 0.03617 0.02531 -0.0653 0.6550 0.5910
0.750 0.2526 0.03572 0.02485 -0.0657 0.6515 0.6110
1.250 0.2855 0.03657 0.02577 -0.0628 0.6350 0.6514
1.500 0.3205 0.03602 0.02525 -0.0631 0.6319 0.6807
2.000 0.3475 0.03700 0.02650 -0.0592 0.6152 0.7446
2.250 0.3851 0.03638 0.02611 -0.0593 0.6125 0.8081
2.750 0.4448 0.03793 0.02767 -0.0628 0.5959 1.0000
3.000 0.4825 0.03760 0.02712 -0.0639 0.5932 1.0000
3.500 0.5000 0.04008 0.02938 -0.0609 0.5761 1.0000
3.750 0.5345 0.03989 0.02904 -0.0614 0.5733 1.0000
4.000 0.5182 0.04283 0.03196 -0.0583 0.5597 1.0000
4.250 0.5513 0.04264 0.03165 -0.0585 0.5567 1.0000
4.750 0.5654 0.04590 0.03480 -0.0558 0.5403 1.0000
5.000 0.5995 0.04555 0.03436 -0.0559 0.5378 1.0000
5.500 0.6119 0.04912 0.03786 -0.0534 0.5213 1.0000
5.750 0.6469 0.04862 0.03729 -0.0534 0.5191 1.0000
6.250 0.6584 0.05237 0.04100 -0.0510 0.5025 1.0000
6.750 0.6711 0.05619 0.04481 -0.0490 0.4863 1.0000
7.000 0.7047 0.05565 0.04424 -0.0487 0.4838 1.0000
7.500 0.7140 0.05995 0.04856 -0.0468 0.4673 1.0000
8.000 0.7230 0.06445 0.05309 -0.0452 0.4510 1.0000
8.250 0.7536 0.06416 0.05279 -0.0448 0.4482 1.0000
8.750 0.7578 0.06937 0.05805 -0.0434 0.4314 1.0000
9.000 0.7882 0.06908 0.05778 -0.0430 0.4290 1.0000
9.500 0.7888 0.07486 0.06364 -0.0419 0.4118 1.0000
9.750 0.7671 0.08030 0.06914 -0.0417 0.3996 1.0000
10.000 0.7863 0.08128 0.07015 -0.0413 0.3950 1.0000
10.250 0.8147 0.08118 0.07007 -0.0407 0.3923 1.0000
10.750 0.8099 0.08805 0.07705 -0.0405 0.3754 1.0000
11.000 0.8386 0.08790 0.07695 -0.0399 0.3731 1.0000
11.250 0.8065 0.09501 0.08412 -0.0407 0.3598 1.0000
11.500 0.8323 0.09513 0.08429 -0.0402 0.3565 1.0000
11.750 0.8105 0.10116 0.09039 -0.0410 0.3454 1.0000
12.000 0.8303 0.10195 0.09123 -0.0406 0.3407 1.0000
12.250 0.8567 0.10180 0.09112 -0.0399 0.3373 1.0000
12.500 0.8372 0.10744 0.09684 -0.0409 0.3252 1.0000
12.750 0.8687 0.10636 0.09581 -0.0398 0.3218 1.0000
13.000 0.8505 0.11188 0.10140 -0.0410 0.3095 1.0000
13.250 0.8819 0.11057 0.10015 -0.0398 0.3056 1.0000
13.500 0.8663 0.11586 0.10551 -0.0411 0.2935 1.0000
13.750 0.8965 0.11454 0.10423 -0.0399 0.2895 1.0000
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Polar data table (+)
Polar graphs
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