GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 100,000 Max Cl/Cd: 53.82 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe92-il-100000.txt Download as CSV file: xf-goe92-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2666 0.09502 0.09079 -0.0252 1.0000 0.0402
-7.250 -0.2710 0.09318 0.08905 -0.0242 1.0000 0.0409
-7.000 -0.2785 0.09164 0.08762 -0.0227 1.0000 0.0416
-6.750 -0.2867 0.09018 0.08624 -0.0212 1.0000 0.0423
-6.500 -0.2944 0.08867 0.08481 -0.0200 1.0000 0.0431
-6.250 -0.2999 0.08702 0.08322 -0.0194 1.0000 0.0440
-6.000 -0.3023 0.08531 0.08156 -0.0200 1.0000 0.0452
-5.750 -0.2991 0.08396 0.08023 -0.0231 1.0000 0.0464
-5.500 -0.2866 0.08330 0.07947 -0.0291 1.0000 0.0473
-5.250 -0.2754 0.08104 0.07714 -0.0321 0.9996 0.0477
-5.000 -0.2597 0.07301 0.06929 -0.0312 0.9936 0.0499
-4.750 -0.2153 0.06775 0.06393 -0.0390 0.9843 0.0540
-4.500 -0.1309 0.06497 0.06050 -0.0579 0.9720 0.0611
-4.250 -0.1122 0.05768 0.05347 -0.0594 0.9637 0.0636
-4.000 -0.0643 0.05336 0.04902 -0.0665 0.9565 0.0717
-3.750 -0.0201 0.04904 0.04451 -0.0729 0.9455 0.0794
-3.500 0.0253 0.04526 0.04051 -0.0789 0.9356 0.0940
-3.250 0.0838 0.04223 0.03701 -0.0868 0.9287 0.1195
-3.000 0.1164 0.03831 0.03316 -0.0892 0.9169 0.1379
-2.750 0.1536 0.03575 0.03039 -0.0922 0.9042 0.1784
-2.000 0.2179 0.02866 0.02361 -0.0884 0.8585 0.3954
-1.750 0.2358 0.02659 0.02162 -0.0852 0.8405 0.4550
-1.500 0.2570 0.02448 0.01953 -0.0827 0.8205 0.4925
-1.250 0.3469 0.02353 0.01648 -0.0931 0.8016 0.2171
-1.000 0.3861 0.02247 0.01443 -0.0912 0.7810 0.1321
-0.750 0.4147 0.02101 0.01262 -0.0897 0.7587 0.1150
-0.500 0.4417 0.01990 0.01124 -0.0883 0.7338 0.1112
-0.250 0.4693 0.01910 0.01006 -0.0869 0.7088 0.1066
0.000 0.4963 0.01859 0.00922 -0.0855 0.6838 0.1033
0.250 0.5223 0.01797 0.00839 -0.0844 0.6582 0.1022
0.500 0.5477 0.01761 0.00785 -0.0833 0.6331 0.1022
0.750 0.5728 0.01736 0.00741 -0.0823 0.6107 0.1072
1.000 0.5983 0.01734 0.00719 -0.0815 0.5891 0.1116
1.250 0.6251 0.01746 0.00703 -0.0809 0.5711 0.1158
1.500 0.6521 0.01759 0.00696 -0.0805 0.5555 0.1249
1.750 0.6763 0.01665 0.00713 -0.0802 0.5420 0.5759
2.000 0.7094 0.01627 0.00718 -0.0805 0.5289 1.0000
2.250 0.7358 0.01671 0.00736 -0.0801 0.5179 1.0000
2.500 0.7623 0.01714 0.00755 -0.0798 0.5087 1.0000
2.750 0.7886 0.01756 0.00784 -0.0795 0.4995 1.0000
3.000 0.8148 0.01804 0.00820 -0.0793 0.4917 1.0000
3.250 0.8413 0.01849 0.00855 -0.0791 0.4848 1.0000
3.500 0.8675 0.01901 0.00900 -0.0790 0.4786 1.0000
3.750 0.8936 0.01950 0.00949 -0.0788 0.4721 1.0000
4.000 0.9203 0.02000 0.00989 -0.0787 0.4667 1.0000
4.250 0.9453 0.02053 0.01050 -0.0785 0.4599 1.0000
4.500 0.9718 0.02100 0.01090 -0.0783 0.4546 1.0000
4.750 0.9967 0.02159 0.01157 -0.0781 0.4485 1.0000
5.000 1.0223 0.02204 0.01206 -0.0778 0.4421 1.0000
5.250 1.0475 0.02255 0.01259 -0.0775 0.4358 1.0000
5.500 1.0723 0.02303 0.01314 -0.0772 0.4288 1.0000
5.750 1.0981 0.02349 0.01358 -0.0769 0.4228 1.0000
6.000 1.1217 0.02397 0.01424 -0.0764 0.4150 1.0000
6.250 1.1474 0.02438 0.01463 -0.0761 0.4086 1.0000
6.500 1.1704 0.02495 0.01540 -0.0756 0.4015 1.0000
6.750 1.1967 0.02531 0.01572 -0.0754 0.3949 1.0000
7.000 1.2205 0.02520 0.01558 -0.0745 0.3816 1.0000
7.250 1.2426 0.02514 0.01555 -0.0735 0.3678 1.0000
7.500 1.2636 0.02540 0.01600 -0.0726 0.3567 1.0000
7.750 1.2847 0.02526 0.01587 -0.0714 0.3415 1.0000
8.000 1.3047 0.02514 0.01578 -0.0701 0.3255 1.0000
8.250 1.3239 0.02526 0.01608 -0.0688 0.3121 1.0000
8.500 1.3420 0.02534 0.01632 -0.0673 0.2973 1.0000
8.750 1.3570 0.02536 0.01652 -0.0654 0.2765 1.0000
9.000 1.3719 0.02549 0.01682 -0.0636 0.2488 1.0000
9.250 1.3872 0.02597 0.01737 -0.0619 0.2104 1.0000
9.500 1.3885 0.02772 0.01855 -0.0590 0.1474 1.0000
9.750 1.3894 0.02987 0.02045 -0.0562 0.1112 1.0000
10.250 1.3705 0.03521 0.02545 -0.0492 0.0469 1.0000
10.500 1.3639 0.03786 0.02823 -0.0468 0.0431 1.0000
10.750 1.3596 0.04050 0.03107 -0.0451 0.0408 1.0000
11.000 1.3532 0.04358 0.03438 -0.0440 0.0391 1.0000
11.250 1.3445 0.04719 0.03821 -0.0434 0.0381 1.0000
11.500 1.3340 0.05139 0.04263 -0.0436 0.0375 1.0000
11.750 1.3216 0.05627 0.04773 -0.0445 0.0371 1.0000
12.000 1.3078 0.06169 0.05336 -0.0461 0.0369 1.0000
12.250 1.2930 0.06750 0.05936 -0.0479 0.0367 1.0000
12.500 1.2779 0.07342 0.06547 -0.0497 0.0366 1.0000
12.750 1.2635 0.07928 0.07149 -0.0515 0.0365 1.0000
13.000 1.2502 0.08496 0.07732 -0.0531 0.0363 1.0000
13.250 1.2386 0.09039 0.08289 -0.0546 0.0362 1.0000
13.500 1.2290 0.09550 0.08812 -0.0559 0.0359 1.0000
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Polar data table (+)
Polar graphs
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