GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.97 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe442-il-1000000.txt Download as CSV file: xf-goe442-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3672 0.09290 0.09131 -0.0207 1.0000 0.0120
-8.250 -0.3694 0.09029 0.08873 -0.0202 1.0000 0.0114
-7.750 -0.3953 0.08525 0.08377 -0.0178 1.0000 0.0132
-7.500 -0.3787 0.08017 0.07869 -0.0246 0.9975 0.0132
-7.250 -0.3895 0.01920 0.01601 -0.0810 0.9843 0.0104
-7.000 -0.3653 0.01668 0.01313 -0.0814 0.9812 0.0108
-6.750 -0.3360 0.01597 0.01232 -0.0820 0.9784 0.0113
-6.500 -0.3052 0.01463 0.01076 -0.0830 0.9762 0.0117
-6.250 -0.2725 0.01350 0.00941 -0.0842 0.9745 0.0123
-6.000 -0.2387 0.01251 0.00823 -0.0856 0.9732 0.0128
-5.750 -0.2026 0.01187 0.00744 -0.0873 0.9721 0.0132
-5.500 -0.1683 0.01046 0.00581 -0.0888 0.9708 0.0142
-5.250 -0.1429 0.01009 0.00541 -0.0881 0.9650 0.0150
-5.000 -0.1105 0.00974 0.00502 -0.0888 0.9614 0.0161
-4.750 -0.0777 0.00946 0.00467 -0.0897 0.9583 0.0170
-4.500 -0.0502 0.00880 0.00394 -0.0895 0.9532 0.0188
-4.250 -0.0223 0.00855 0.00368 -0.0892 0.9470 0.0202
-4.000 0.0094 0.00833 0.00340 -0.0898 0.9422 0.0217
-3.750 0.0343 0.00794 0.00299 -0.0889 0.9331 0.0241
-3.500 0.0637 0.00786 0.00290 -0.0890 0.9255 0.0265
-3.250 0.0912 0.00762 0.00262 -0.0886 0.9147 0.0289
-3.000 0.1186 0.00747 0.00246 -0.0883 0.9019 0.0319
-2.750 0.1463 0.00742 0.00237 -0.0879 0.8869 0.0344
-2.500 0.1731 0.00725 0.00211 -0.0874 0.8683 0.0370
-2.250 0.1991 0.00715 0.00194 -0.0868 0.8437 0.0400
-2.000 0.2248 0.00717 0.00186 -0.0860 0.8145 0.0427
-1.750 0.2499 0.00724 0.00179 -0.0851 0.7828 0.0446
-1.500 0.2739 0.00717 0.00155 -0.0841 0.7482 0.0476
-1.250 0.2975 0.00723 0.00144 -0.0830 0.7063 0.0510
-1.000 0.3210 0.00738 0.00139 -0.0819 0.6540 0.0541
-0.750 0.3441 0.00761 0.00136 -0.0807 0.5928 0.0565
-0.500 0.3685 0.00767 0.00125 -0.0799 0.5565 0.0609
-0.250 0.3942 0.00770 0.00120 -0.0793 0.5342 0.0664
0.000 0.4204 0.00777 0.00119 -0.0788 0.5170 0.0705
0.250 0.4465 0.00775 0.00113 -0.0783 0.5015 0.0815
0.500 0.4718 0.00754 0.00114 -0.0778 0.4878 0.1797
0.750 0.4969 0.00731 0.00121 -0.0773 0.4752 0.3131
1.000 0.5202 0.00691 0.00129 -0.0765 0.4624 0.5206
1.250 0.5843 0.00598 0.00141 -0.0848 0.4427 1.0000
1.500 0.6095 0.00609 0.00144 -0.0841 0.4303 1.0000
1.750 0.6347 0.00621 0.00148 -0.0834 0.4162 1.0000
2.000 0.6598 0.00634 0.00153 -0.0827 0.4024 1.0000
2.250 0.6850 0.00647 0.00159 -0.0820 0.3900 1.0000
2.500 0.7101 0.00661 0.00166 -0.0813 0.3779 1.0000
2.750 0.7355 0.00673 0.00173 -0.0807 0.3662 1.0000
3.000 0.7607 0.00686 0.00181 -0.0800 0.3548 1.0000
3.250 0.7858 0.00700 0.00190 -0.0794 0.3434 1.0000
3.500 0.8108 0.00716 0.00200 -0.0787 0.3309 1.0000
3.750 0.8357 0.00733 0.00212 -0.0780 0.3171 1.0000
4.000 0.8605 0.00751 0.00223 -0.0773 0.3028 1.0000
4.250 0.8853 0.00770 0.00236 -0.0767 0.2873 1.0000
4.500 0.9098 0.00792 0.00250 -0.0760 0.2678 1.0000
4.750 0.9333 0.00824 0.00269 -0.0751 0.2393 1.0000
5.000 0.9547 0.00878 0.00297 -0.0740 0.1915 1.0000
5.250 0.9766 0.00928 0.00329 -0.0729 0.1577 1.0000
5.500 1.0002 0.00961 0.00356 -0.0721 0.1438 1.0000
5.750 1.0241 0.00992 0.00382 -0.0713 0.1352 1.0000
6.000 1.0489 0.01012 0.00404 -0.0707 0.1316 1.0000
6.250 1.0733 0.01037 0.00428 -0.0700 0.1276 1.0000
6.500 1.0969 0.01070 0.00459 -0.0693 0.1218 1.0000
6.750 1.1218 0.01088 0.00480 -0.0687 0.1193 1.0000
7.000 1.1464 0.01109 0.00502 -0.0681 0.1153 1.0000
7.250 1.1700 0.01139 0.00530 -0.0674 0.1104 1.0000
7.500 1.1939 0.01167 0.00560 -0.0667 0.1069 1.0000
7.750 1.2189 0.01182 0.00579 -0.0662 0.1040 1.0000
8.000 1.2429 0.01206 0.00604 -0.0655 0.1002 1.0000
8.250 1.2660 0.01239 0.00636 -0.0648 0.0951 1.0000
8.500 1.2906 0.01256 0.00658 -0.0642 0.0914 1.0000
8.750 1.3138 0.01286 0.00685 -0.0635 0.0835 1.0000
9.000 1.3358 0.01326 0.00717 -0.0626 0.0700 1.0000
9.250 1.3482 0.01451 0.00812 -0.0603 0.0317 1.0000
9.500 1.3641 0.01544 0.00899 -0.0584 0.0193 1.0000
9.750 1.3829 0.01606 0.00963 -0.0570 0.0161 1.0000
10.000 1.4008 0.01675 0.01036 -0.0554 0.0136 1.0000
10.250 1.4198 0.01729 0.01096 -0.0541 0.0125 1.0000
10.500 1.4369 0.01796 0.01168 -0.0524 0.0115 1.0000
10.750 1.4501 0.01892 0.01273 -0.0502 0.0104 1.0000
11.000 1.4668 0.01952 0.01341 -0.0485 0.0100 1.0000
11.250 1.4821 0.02017 0.01413 -0.0466 0.0095 1.0000
11.500 1.4943 0.02084 0.01487 -0.0442 0.0091 1.0000
11.750 1.5044 0.02158 0.01567 -0.0415 0.0087 1.0000
12.000 1.5124 0.02245 0.01661 -0.0387 0.0082 1.0000
12.250 1.5167 0.02355 0.01780 -0.0354 0.0079 1.0000
12.500 1.5117 0.02525 0.01965 -0.0313 0.0075 1.0000
12.750 1.5209 0.02614 0.02063 -0.0291 0.0073 1.0000
13.000 1.5281 0.02721 0.02178 -0.0270 0.0071 1.0000
13.250 1.5304 0.02865 0.02333 -0.0245 0.0070 1.0000
13.500 1.5340 0.03011 0.02488 -0.0225 0.0068 1.0000
13.750 1.5357 0.03182 0.02670 -0.0207 0.0066 1.0000
14.000 1.5360 0.03379 0.02876 -0.0192 0.0064 1.0000
14.250 1.5322 0.03633 0.03142 -0.0180 0.0064 1.0000
14.500 1.5291 0.03905 0.03426 -0.0173 0.0062 1.0000
14.750 1.5280 0.04179 0.03709 -0.0171 0.0060 1.0000
15.000 1.5198 0.04563 0.04106 -0.0175 0.0060 1.0000
15.250 1.5124 0.04973 0.04527 -0.0185 0.0059 1.0000
15.500 1.5030 0.05441 0.05008 -0.0201 0.0058 1.0000
15.750 1.4890 0.06000 0.05582 -0.0222 0.0058 1.0000
16.000 1.4723 0.06616 0.06211 -0.0247 0.0057 1.0000
16.250 1.4557 0.07238 0.06845 -0.0273 0.0056 1.0000
16.500 1.4386 0.07882 0.07501 -0.0300 0.0056 1.0000
16.750 1.4189 0.08587 0.08219 -0.0331 0.0056 1.0000
17.000 1.4013 0.09281 0.08925 -0.0363 0.0056 1.0000
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