GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 100,000 Max Cl/Cd: 52.22 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe590-il-100000.txt Download as CSV file: xf-goe590-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 590 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4103 0.09538 0.09069 -0.0107 1.0000 0.0455
-7.500 -0.4083 0.09267 0.08804 -0.0121 1.0000 0.0469
-7.250 -0.4058 0.09014 0.08557 -0.0144 1.0000 0.0485
-7.000 -0.3991 0.08823 0.08368 -0.0192 1.0000 0.0499
-6.750 -0.3874 0.08697 0.08238 -0.0252 1.0000 0.0506
-6.500 -0.3790 0.08239 0.07784 -0.0268 1.0000 0.0514
-6.250 -0.3755 0.07671 0.07227 -0.0218 1.0000 0.0550
-6.000 -0.3648 0.07354 0.06911 -0.0231 1.0000 0.0575
-5.750 -0.3514 0.07058 0.06612 -0.0253 1.0000 0.0608
-5.500 -0.3225 0.07082 0.06602 -0.0324 1.0000 0.0639
-5.250 -0.3185 0.06464 0.06002 -0.0307 1.0000 0.0651
-5.000 -0.3118 0.06074 0.05617 -0.0289 1.0000 0.0676
-4.750 -0.2991 0.05787 0.05328 -0.0287 1.0000 0.0717
-4.500 -0.2702 0.05765 0.05263 -0.0321 1.0000 0.0777
-4.250 -0.2693 0.05260 0.04782 -0.0296 1.0000 0.0796
-4.000 -0.2656 0.05014 0.04543 -0.0273 1.0000 0.0829
-3.750 -0.2584 0.04953 0.04465 -0.0257 1.0000 0.0898
-3.500 -0.2385 0.04586 0.04093 -0.0274 0.9947 0.0940
-3.250 -0.1936 0.04195 0.03685 -0.0330 0.9830 0.1105
-3.000 -0.1447 0.03880 0.03333 -0.0387 0.9700 0.1339
-2.750 -0.1028 0.03514 0.02951 -0.0428 0.9572 0.1540
-2.500 -0.0594 0.03214 0.02624 -0.0469 0.9440 0.1891
-1.750 0.0825 0.02296 0.01515 -0.0531 0.8996 0.1006
-1.500 0.1161 0.02121 0.01293 -0.0531 0.8791 0.1009
-1.250 0.1485 0.01968 0.01096 -0.0528 0.8603 0.1006
-1.000 0.1776 0.01849 0.00944 -0.0521 0.8404 0.1014
-0.750 0.2057 0.01763 0.00829 -0.0513 0.8219 0.1054
-0.500 0.2321 0.01703 0.00761 -0.0506 0.8053 0.1175
-0.250 0.2582 0.01627 0.00683 -0.0497 0.7902 0.1242
0.000 0.2840 0.01573 0.00623 -0.0488 0.7757 0.1381
0.250 0.3089 0.01492 0.00559 -0.0478 0.7629 0.2121
0.500 0.3992 0.01296 0.00505 -0.0604 0.7495 1.0000
0.750 0.4227 0.01323 0.00515 -0.0595 0.7372 1.0000
1.000 0.4464 0.01351 0.00530 -0.0587 0.7258 1.0000
1.250 0.4702 0.01381 0.00549 -0.0580 0.7157 1.0000
1.500 0.4943 0.01411 0.00566 -0.0572 0.7072 1.0000
1.750 0.5181 0.01443 0.00595 -0.0565 0.6975 1.0000
2.000 0.5421 0.01477 0.00626 -0.0559 0.6890 1.0000
2.250 0.5664 0.01510 0.00659 -0.0552 0.6818 1.0000
2.500 0.5903 0.01549 0.00703 -0.0548 0.6736 1.0000
2.750 0.6147 0.01583 0.00734 -0.0541 0.6673 1.0000
3.000 0.6384 0.01627 0.00790 -0.0537 0.6595 1.0000
3.250 0.6629 0.01665 0.00831 -0.0530 0.6538 1.0000
3.500 0.6864 0.01716 0.00897 -0.0526 0.6465 1.0000
3.750 0.7109 0.01758 0.00955 -0.0520 0.6409 1.0000
4.000 0.7339 0.01802 0.01016 -0.0513 0.6321 1.0000
4.250 0.7564 0.01758 0.00965 -0.0488 0.6124 1.0000
4.500 0.7778 0.01741 0.00960 -0.0468 0.5921 1.0000
4.750 0.7971 0.01645 0.00850 -0.0432 0.5517 1.0000
5.000 0.8115 0.01554 0.00752 -0.0386 0.4783 1.0000
5.250 0.8044 0.01824 0.00807 -0.0330 0.0998 1.0000
5.500 0.8179 0.02004 0.00987 -0.0306 0.0766 1.0000
5.750 0.8318 0.02150 0.01150 -0.0282 0.0672 1.0000
6.000 0.8428 0.02317 0.01315 -0.0257 0.0595 1.0000
6.250 0.8598 0.02466 0.01465 -0.0234 0.0561 1.0000
6.500 0.8818 0.02647 0.01641 -0.0218 0.0541 1.0000
6.750 0.9083 0.02867 0.01863 -0.0207 0.0530 1.0000
7.000 0.9354 0.03262 0.02252 -0.0207 0.0488 1.0000
7.250 0.9609 0.03551 0.02564 -0.0197 0.0488 1.0000
7.500 0.9845 0.03661 0.02744 -0.0171 0.0531 1.0000
7.750 1.0084 0.04134 0.03250 -0.0158 0.0596 1.0000
11.250 0.7297 0.12009 0.11550 -0.0254 0.1941 1.0000
11.500 0.7210 0.12412 0.11950 -0.0266 0.1824 1.0000
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Polar data table (+)
Polar graphs
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