GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 100,000 Max Cl/Cd: 54.99 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe92-il-100000-n5.txt Download as CSV file: xf-goe92-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2434 0.09913 0.09490 -0.0273 1.0000 0.0267
-7.500 -0.2503 0.09784 0.09372 -0.0259 1.0000 0.0271
-7.250 -0.2637 0.09717 0.09316 -0.0231 1.0000 0.0273
-7.000 -0.2548 0.09484 0.09088 -0.0276 0.9931 0.0278
-6.750 -0.2265 0.09126 0.08727 -0.0382 0.9821 0.0282
-6.500 -0.1955 0.08728 0.08324 -0.0480 0.9724 0.0285
-6.250 -0.1624 0.08291 0.07879 -0.0567 0.9640 0.0286
-6.000 -0.1299 0.07839 0.07418 -0.0639 0.9552 0.0286
-5.750 -0.1119 0.07268 0.06850 -0.0659 0.9462 0.0290
-5.500 -0.0919 0.06771 0.06352 -0.0674 0.9381 0.0298
-5.250 -0.0662 0.06362 0.05936 -0.0710 0.9267 0.0307
-5.000 -0.0383 0.05977 0.05542 -0.0752 0.9141 0.0317
-4.750 -0.0095 0.05612 0.05164 -0.0793 0.9012 0.0330
-4.500 0.0199 0.05266 0.04803 -0.0830 0.8885 0.0347
-4.250 0.0695 0.05099 0.04579 -0.0895 0.8758 0.0387
-4.000 0.0827 0.04590 0.04080 -0.0899 0.8646 0.0406
-3.750 0.1045 0.04309 0.03791 -0.0906 0.8522 0.0437
-3.500 0.1451 0.04224 0.03642 -0.0930 0.8388 0.0513
-3.250 0.1642 0.03771 0.03191 -0.0936 0.8253 0.0536
-3.000 0.1863 0.03526 0.02937 -0.0938 0.8097 0.0584
-2.750 0.2120 0.03316 0.02703 -0.0943 0.7928 0.0728
-2.250 0.2750 0.02791 0.02084 -0.0938 0.7572 0.0465
-2.000 0.3040 0.02577 0.01825 -0.0934 0.7368 0.0446
-1.750 0.3326 0.02423 0.01626 -0.0929 0.7135 0.0474
-1.500 0.3612 0.02261 0.01415 -0.0922 0.6905 0.0464
-1.250 0.3895 0.02153 0.01255 -0.0915 0.6676 0.0490
-1.000 0.4173 0.02077 0.01130 -0.0907 0.6451 0.0508
-0.750 0.4444 0.01991 0.01005 -0.0901 0.6242 0.0511
-0.500 0.4710 0.01920 0.00903 -0.0894 0.6043 0.0520
-0.250 0.4967 0.01839 0.00809 -0.0890 0.5853 0.0567
0.000 0.5228 0.01796 0.00747 -0.0884 0.5674 0.0572
0.250 0.5485 0.01761 0.00696 -0.0878 0.5506 0.0572
0.500 0.5742 0.01735 0.00656 -0.0872 0.5347 0.0575
0.750 0.5997 0.01720 0.00624 -0.0867 0.5193 0.0581
1.000 0.6256 0.01714 0.00599 -0.0862 0.5043 0.0593
1.250 0.6520 0.01716 0.00580 -0.0858 0.4897 0.0610
1.500 0.6784 0.01722 0.00567 -0.0855 0.4758 0.0635
1.750 0.7049 0.01729 0.00561 -0.0852 0.4631 0.0690
2.000 0.7313 0.01736 0.00561 -0.0850 0.4518 0.0865
2.250 0.7585 0.01571 0.00574 -0.0851 0.4424 1.0000
2.500 0.7844 0.01600 0.00583 -0.0847 0.4334 1.0000
2.750 0.8104 0.01631 0.00597 -0.0844 0.4256 1.0000
3.000 0.8362 0.01662 0.00613 -0.0841 0.4185 1.0000
3.250 0.8621 0.01695 0.00634 -0.0838 0.4117 1.0000
3.500 0.8879 0.01728 0.00659 -0.0836 0.4053 1.0000
3.750 0.9136 0.01763 0.00683 -0.0833 0.3999 1.0000
4.000 0.9394 0.01797 0.00716 -0.0831 0.3941 1.0000
4.250 0.9650 0.01833 0.00746 -0.0829 0.3891 1.0000
4.500 0.9906 0.01871 0.00782 -0.0826 0.3842 1.0000
4.750 1.0160 0.01908 0.00821 -0.0824 0.3786 1.0000
5.000 1.0412 0.01946 0.00855 -0.0821 0.3733 1.0000
5.250 1.0662 0.01984 0.00901 -0.0818 0.3673 1.0000
5.500 1.0910 0.02022 0.00942 -0.0815 0.3615 1.0000
5.750 1.1159 0.02064 0.00982 -0.0812 0.3568 1.0000
6.000 1.1406 0.02105 0.01037 -0.0809 0.3516 1.0000
6.250 1.1652 0.02147 0.01090 -0.0805 0.3467 1.0000
6.500 1.1899 0.02191 0.01136 -0.0802 0.3423 1.0000
6.750 1.2126 0.02228 0.01192 -0.0796 0.3340 1.0000
7.000 1.2317 0.02249 0.01215 -0.0784 0.3169 1.0000
7.250 1.2503 0.02276 0.01248 -0.0772 0.2993 1.0000
7.500 1.2697 0.02309 0.01292 -0.0761 0.2821 1.0000
7.750 1.2896 0.02345 0.01344 -0.0752 0.2614 1.0000
8.000 1.3079 0.02395 0.01397 -0.0740 0.2284 1.0000
8.250 1.3103 0.02585 0.01513 -0.0714 0.1422 1.0000
8.500 1.3168 0.02775 0.01685 -0.0691 0.1076 1.0000
8.750 1.3101 0.03064 0.01931 -0.0657 0.0285 1.0000
9.000 1.3111 0.03246 0.02121 -0.0627 0.0229 1.0000
9.250 1.3162 0.03398 0.02293 -0.0603 0.0211 1.0000
9.500 1.3198 0.03567 0.02486 -0.0581 0.0202 1.0000
9.750 1.3213 0.03764 0.02707 -0.0561 0.0194 1.0000
10.000 1.3203 0.03994 0.02962 -0.0544 0.0186 1.0000
10.250 1.3167 0.04267 0.03258 -0.0530 0.0178 1.0000
10.500 1.3104 0.04588 0.03603 -0.0521 0.0170 1.0000
10.750 1.3017 0.04964 0.04003 -0.0517 0.0164 1.0000
11.000 1.2911 0.05401 0.04463 -0.0521 0.0160 1.0000
11.250 1.2789 0.05899 0.04984 -0.0531 0.0157 1.0000
11.500 1.2657 0.06445 0.05551 -0.0546 0.0156 1.0000
11.750 1.2516 0.07021 0.06147 -0.0563 0.0155 1.0000
12.000 1.2372 0.07616 0.06761 -0.0581 0.0154 1.0000
12.250 1.2230 0.08212 0.07374 -0.0599 0.0154 1.0000
12.500 1.2097 0.08804 0.07983 -0.0617 0.0153 1.0000
12.750 1.1974 0.09386 0.08580 -0.0634 0.0152 1.0000
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Polar data table (+)
Polar graphs
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