GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 436 AIRFOIL (goe436-il) Reynolds number: 100,000 Max Cl/Cd: 51.65 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe436-il-100000-n5.txt Download as CSV file: xf-goe436-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 436 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3582 0.09260 0.08746 -0.0388 1.0000 0.0587
-8.750 -0.3659 0.08945 0.08438 -0.0391 1.0000 0.0589
-8.500 -0.3766 0.08648 0.08150 -0.0389 1.0000 0.0589
-8.250 -0.3890 0.08395 0.07906 -0.0377 1.0000 0.0586
-8.000 -0.4065 0.08166 0.07687 -0.0358 1.0000 0.0583
-7.750 -0.4206 0.07891 0.07420 -0.0349 1.0000 0.0579
-7.500 -0.4345 0.07590 0.07123 -0.0342 1.0000 0.0575
-7.250 -0.4259 0.07000 0.06525 -0.0406 0.9944 0.0575
-7.000 -0.4095 0.06219 0.05719 -0.0498 0.9856 0.0588
-6.750 -0.3937 0.05494 0.04955 -0.0562 0.9769 0.0595
-6.500 -0.3752 0.04891 0.04310 -0.0604 0.9696 0.0597
-6.250 -0.3557 0.04372 0.03740 -0.0633 0.9622 0.0611
-6.000 -0.3290 0.04242 0.03612 -0.0645 0.9570 0.0626
-5.750 -0.3051 0.04002 0.03351 -0.0656 0.9501 0.0637
-5.500 -0.2757 0.03688 0.02998 -0.0678 0.9455 0.0644
-5.250 -0.2545 0.03449 0.02727 -0.0678 0.9371 0.0653
-5.000 -0.2225 0.03229 0.02469 -0.0695 0.9317 0.0672
-4.750 -0.1952 0.03034 0.02234 -0.0700 0.9231 0.0693
-4.500 -0.1601 0.02823 0.01978 -0.0716 0.9164 0.0706
-4.250 -0.1291 0.02659 0.01772 -0.0722 0.9075 0.0718
-4.000 -0.0924 0.02502 0.01584 -0.0738 0.9001 0.0734
-3.750 -0.0628 0.02396 0.01474 -0.0742 0.8896 0.0757
-3.500 -0.0253 0.02292 0.01356 -0.0758 0.8829 0.0782
-3.250 0.0020 0.02204 0.01254 -0.0755 0.8720 0.0800
-3.000 0.0341 0.02115 0.01150 -0.0760 0.8637 0.0821
-2.750 0.0658 0.02041 0.01060 -0.0763 0.8545 0.0848
-2.500 0.0949 0.01969 0.00982 -0.0763 0.8440 0.0878
-2.250 0.1279 0.01897 0.00912 -0.0770 0.8354 0.0911
-2.000 0.1556 0.01843 0.00856 -0.0767 0.8233 0.0939
-1.750 0.1836 0.01794 0.00804 -0.0763 0.8111 0.0974
-1.500 0.2122 0.01750 0.00755 -0.0761 0.7990 0.1020
-1.250 0.2403 0.01704 0.00713 -0.0758 0.7862 0.1079
-1.000 0.2673 0.01670 0.00674 -0.0753 0.7719 0.1135
-0.750 0.2929 0.01637 0.00640 -0.0745 0.7561 0.1200
-0.500 0.3189 0.01611 0.00611 -0.0738 0.7394 0.1315
-0.250 0.3442 0.01581 0.00587 -0.0730 0.7211 0.1495
0.000 0.3702 0.01539 0.00562 -0.0724 0.7021 0.1948
0.500 0.4850 0.01324 0.00537 -0.0832 0.6569 1.0000
0.750 0.5084 0.01336 0.00525 -0.0820 0.6353 1.0000
1.000 0.5317 0.01353 0.00519 -0.0809 0.6147 1.0000
1.250 0.5544 0.01372 0.00518 -0.0796 0.5943 1.0000
1.500 0.5767 0.01392 0.00523 -0.0784 0.5740 1.0000
1.750 0.5990 0.01415 0.00529 -0.0771 0.5542 1.0000
2.000 0.6213 0.01438 0.00536 -0.0759 0.5356 1.0000
2.250 0.6438 0.01463 0.00546 -0.0747 0.5186 1.0000
2.500 0.6665 0.01488 0.00558 -0.0736 0.5037 1.0000
2.750 0.6894 0.01515 0.00572 -0.0726 0.4905 1.0000
3.000 0.7126 0.01543 0.00590 -0.0716 0.4788 1.0000
3.250 0.7359 0.01573 0.00607 -0.0707 0.4686 1.0000
3.500 0.7594 0.01604 0.00630 -0.0698 0.4586 1.0000
3.750 0.7832 0.01636 0.00655 -0.0690 0.4503 1.0000
4.000 0.8071 0.01668 0.00683 -0.0682 0.4425 1.0000
4.250 0.8313 0.01704 0.00711 -0.0675 0.4355 1.0000
4.500 0.8552 0.01738 0.00746 -0.0668 0.4280 1.0000
4.750 0.8799 0.01777 0.00776 -0.0662 0.4221 1.0000
5.000 0.9038 0.01812 0.00816 -0.0655 0.4154 1.0000
5.250 0.9281 0.01850 0.00854 -0.0648 0.4092 1.0000
5.500 0.9525 0.01891 0.00894 -0.0642 0.4035 1.0000
5.750 0.9761 0.01930 0.00939 -0.0635 0.3971 1.0000
6.000 1.0002 0.01971 0.00977 -0.0628 0.3905 1.0000
6.250 1.0211 0.02005 0.01020 -0.0616 0.3807 1.0000
6.500 1.0423 0.02039 0.01052 -0.0605 0.3709 1.0000
6.750 1.0625 0.02070 0.01088 -0.0592 0.3604 1.0000
7.000 1.0829 0.02105 0.01130 -0.0579 0.3509 1.0000
7.250 1.1041 0.02141 0.01169 -0.0568 0.3433 1.0000
7.500 1.1256 0.02181 0.01221 -0.0558 0.3365 1.0000
7.750 1.1466 0.02220 0.01269 -0.0547 0.3296 1.0000
8.000 1.1673 0.02261 0.01319 -0.0535 0.3229 1.0000
8.250 1.1865 0.02300 0.01371 -0.0522 0.3144 1.0000
8.500 1.2045 0.02338 0.01418 -0.0506 0.3050 1.0000
8.750 1.2217 0.02376 0.01463 -0.0489 0.2955 1.0000
9.000 1.2392 0.02420 0.01525 -0.0473 0.2862 1.0000
9.250 1.2559 0.02465 0.01577 -0.0456 0.2781 1.0000
9.500 1.2718 0.02513 0.01643 -0.0439 0.2682 1.0000
9.750 1.2857 0.02562 0.01705 -0.0418 0.2569 1.0000
10.000 1.2966 0.02615 0.01769 -0.0393 0.2436 1.0000
10.250 1.3056 0.02676 0.01838 -0.0365 0.2300 1.0000
10.500 1.3131 0.02748 0.01916 -0.0337 0.2144 1.0000
10.750 1.3182 0.02837 0.02007 -0.0308 0.1972 1.0000
11.000 1.3210 0.02949 0.02117 -0.0279 0.1806 1.0000
11.250 1.3210 0.03089 0.02253 -0.0250 0.1648 1.0000
11.500 1.3192 0.03255 0.02418 -0.0223 0.1499 1.0000
11.750 1.3151 0.03453 0.02615 -0.0198 0.1362 1.0000
12.000 1.3099 0.03675 0.02838 -0.0176 0.1237 1.0000
12.250 1.3046 0.03918 0.03085 -0.0159 0.1125 1.0000
12.500 1.2983 0.04187 0.03358 -0.0145 0.1033 1.0000
12.750 1.2892 0.04502 0.03676 -0.0135 0.0955 1.0000
13.000 1.2836 0.04808 0.03992 -0.0130 0.0880 1.0000
13.250 1.2738 0.05179 0.04368 -0.0130 0.0827 1.0000
13.500 1.2655 0.05558 0.04758 -0.0132 0.0786 1.0000
13.750 1.2547 0.05988 0.05195 -0.0139 0.0753 1.0000
14.000 1.2435 0.06442 0.05655 -0.0149 0.0728 1.0000
14.250 1.2351 0.06875 0.06100 -0.0159 0.0701 1.0000
14.500 1.2251 0.07345 0.06580 -0.0172 0.0674 1.0000
14.750 1.2153 0.07821 0.07061 -0.0186 0.0651 1.0000
15.000 1.2070 0.08273 0.07515 -0.0198 0.0627 1.0000
15.250 1.2027 0.08684 0.07942 -0.0210 0.0598 1.0000
15.500 1.1976 0.09107 0.08375 -0.0222 0.0571 1.0000
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Polar data table (+)
Polar graphs
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