GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 100,000 Max Cl/Cd: 55.5 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe796-il-100000.txt Download as CSV file: xf-goe796-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4013 0.09849 0.09376 -0.0368 1.0000 0.1263
-8.000 -0.4419 0.09792 0.09336 -0.0347 1.0000 0.1267
-7.750 -0.4800 0.09621 0.09174 -0.0357 1.0000 0.1271
-7.500 -0.4864 0.09252 0.08812 -0.0336 1.0000 0.1278
-7.250 -0.4783 0.08966 0.08532 -0.0291 1.0000 0.1288
-7.000 -0.4791 0.08755 0.08326 -0.0257 1.0000 0.1298
-6.750 -0.4842 0.08555 0.08130 -0.0232 1.0000 0.1310
-6.500 -0.4909 0.08340 0.07919 -0.0216 1.0000 0.1324
-6.250 -0.4874 0.08023 0.07602 -0.0230 0.9981 0.1348
-6.000 -0.4821 0.05304 0.04747 -0.0487 0.9881 0.0838
-5.750 -0.4518 0.04833 0.04249 -0.0523 0.9835 0.0809
-5.500 -0.4268 0.04302 0.03671 -0.0550 0.9776 0.0793
-5.250 -0.3958 0.03795 0.03095 -0.0580 0.9730 0.0792
-5.000 -0.3632 0.03397 0.02613 -0.0602 0.9685 0.0816
-4.750 -0.3315 0.03182 0.02367 -0.0617 0.9628 0.0861
-4.500 -0.2924 0.03045 0.02191 -0.0643 0.9584 0.0978
-4.250 -0.2636 0.03005 0.02124 -0.0649 0.9515 0.1113
-4.000 -0.2287 0.02910 0.02029 -0.0670 0.9463 0.1245
-3.750 -0.1915 0.02872 0.01984 -0.0695 0.9416 0.1394
-3.500 -0.1656 0.02825 0.01932 -0.0697 0.9342 0.1501
-3.250 -0.1274 0.02767 0.01857 -0.0721 0.9296 0.1623
-3.000 -0.0963 0.02720 0.01797 -0.0730 0.9236 0.1713
-2.750 -0.0648 0.02651 0.01725 -0.0739 0.9175 0.1793
-2.500 -0.0246 0.02588 0.01655 -0.0764 0.9136 0.1925
-2.250 0.0015 0.02563 0.01628 -0.0764 0.9066 0.2067
-2.000 0.0350 0.02522 0.01594 -0.0777 0.9009 0.2236
-1.750 0.0763 0.02472 0.01556 -0.0804 0.8973 0.2440
-1.500 0.0964 0.02467 0.01559 -0.0793 0.8889 0.2627
-1.250 0.1334 0.02426 0.01537 -0.0812 0.8841 0.3002
-1.000 0.1655 0.02362 0.01522 -0.0822 0.8783 0.3714
-0.750 0.2284 0.02163 0.01512 -0.0871 0.8745 1.0000
-0.500 0.2809 0.02129 0.01448 -0.0912 0.8683 1.0000
-0.250 0.3099 0.02126 0.01426 -0.0911 0.8575 1.0000
0.000 0.3594 0.02076 0.01358 -0.0944 0.8524 1.0000
0.250 0.3779 0.02106 0.01378 -0.0927 0.8418 1.0000
0.500 0.4190 0.02079 0.01338 -0.0947 0.8374 1.0000
0.750 0.4371 0.02115 0.01366 -0.0930 0.8271 1.0000
1.000 0.4767 0.02083 0.01326 -0.0945 0.8224 1.0000
1.250 0.4962 0.02115 0.01352 -0.0930 0.8121 1.0000
1.500 0.5351 0.02077 0.01307 -0.0943 0.8070 1.0000
1.750 0.5553 0.02107 0.01333 -0.0928 0.7965 1.0000
2.000 0.5934 0.02066 0.01288 -0.0939 0.7914 1.0000
2.250 0.6140 0.02093 0.01313 -0.0925 0.7803 1.0000
2.500 0.6533 0.02040 0.01256 -0.0935 0.7751 1.0000
2.750 0.6741 0.02063 0.01278 -0.0920 0.7631 1.0000
3.000 0.7008 0.02063 0.01278 -0.0913 0.7531 1.0000
3.250 0.7351 0.02027 0.01239 -0.0916 0.7453 1.0000
3.500 0.7591 0.02033 0.01247 -0.0904 0.7328 1.0000
3.750 0.7865 0.02021 0.01235 -0.0896 0.7206 1.0000
4.000 0.8168 0.01993 0.01204 -0.0891 0.7086 1.0000
4.250 0.8490 0.01956 0.01162 -0.0888 0.6965 1.0000
4.500 0.8750 0.01948 0.01153 -0.0878 0.6817 1.0000
4.750 0.9008 0.01942 0.01148 -0.0868 0.6663 1.0000
5.000 0.9267 0.01937 0.01141 -0.0858 0.6505 1.0000
5.250 0.9524 0.01932 0.01134 -0.0848 0.6339 1.0000
5.500 0.9748 0.01940 0.01144 -0.0834 0.6152 1.0000
5.750 0.9984 0.01943 0.01149 -0.0822 0.5967 1.0000
6.000 1.0226 0.01952 0.01157 -0.0811 0.5792 1.0000
6.250 1.0470 0.01967 0.01171 -0.0801 0.5623 1.0000
6.500 1.0713 0.01984 0.01185 -0.0791 0.5452 1.0000
6.750 1.0953 0.02004 0.01204 -0.0781 0.5282 1.0000
7.000 1.1188 0.02028 0.01224 -0.0771 0.5109 1.0000
7.250 1.1387 0.02061 0.01259 -0.0755 0.4912 1.0000
7.500 1.1589 0.02091 0.01288 -0.0739 0.4707 1.0000
7.750 1.1799 0.02126 0.01312 -0.0725 0.4506 1.0000
8.000 1.1977 0.02176 0.01363 -0.0707 0.4296 1.0000
8.250 1.2158 0.02230 0.01412 -0.0689 0.4083 1.0000
8.500 1.2334 0.02294 0.01468 -0.0672 0.3868 1.0000
8.750 1.2482 0.02367 0.01540 -0.0650 0.3638 1.0000
9.000 1.2646 0.02450 0.01609 -0.0631 0.3416 1.0000
9.250 1.2766 0.02538 0.01700 -0.0607 0.3190 1.0000
9.500 1.2892 0.02627 0.01784 -0.0583 0.2984 1.0000
9.750 1.3014 0.02716 0.01865 -0.0560 0.2795 1.0000
10.000 1.3097 0.02804 0.01961 -0.0530 0.2615 1.0000
10.250 1.3166 0.02893 0.02052 -0.0499 0.2449 1.0000
10.500 1.3210 0.02987 0.02146 -0.0465 0.2292 1.0000
10.750 1.3248 0.03094 0.02250 -0.0433 0.2141 1.0000
11.000 1.3286 0.03216 0.02367 -0.0404 0.1995 1.0000
11.250 1.3334 0.03355 0.02500 -0.0378 0.1857 1.0000
11.500 1.3398 0.03508 0.02650 -0.0356 0.1727 1.0000
11.750 1.3492 0.03670 0.02806 -0.0338 0.1609 1.0000
12.000 1.3598 0.03833 0.02956 -0.0322 0.1490 1.0000
12.250 1.3579 0.04002 0.03151 -0.0295 0.1396 1.0000
12.500 1.3594 0.04183 0.03339 -0.0273 0.1300 1.0000
12.750 1.3615 0.04360 0.03506 -0.0255 0.1205 1.0000
13.000 1.3562 0.04579 0.03754 -0.0233 0.1118 1.0000
13.250 1.3542 0.04810 0.03991 -0.0216 0.1032 1.0000
13.500 1.3527 0.05038 0.04210 -0.0201 0.0949 1.0000
13.750 1.3468 0.05326 0.04522 -0.0187 0.0872 1.0000
14.000 1.3476 0.05590 0.04780 -0.0174 0.0803 1.0000
14.250 1.3458 0.05879 0.05086 -0.0163 0.0745 1.0000
14.500 1.3526 0.06138 0.05339 -0.0150 0.0691 1.0000
14.750 1.3486 0.06475 0.05705 -0.0141 0.0655 1.0000
15.000 1.3502 0.06755 0.05991 -0.0133 0.0620 1.0000
15.250 1.3563 0.07058 0.06294 -0.0123 0.0586 1.0000
15.500 1.3444 0.07473 0.06743 -0.0120 0.0569 1.0000
15.750 1.3339 0.07894 0.07191 -0.0121 0.0552 1.0000
16.000 1.3234 0.08327 0.07645 -0.0124 0.0537 1.0000
16.250 1.3155 0.08743 0.08079 -0.0129 0.0522 1.0000
16.500 1.3233 0.09004 0.08331 -0.0124 0.0499 1.0000
16.750 1.3078 0.09563 0.08912 -0.0135 0.0492 1.0000
17.000 1.2858 0.10202 0.09580 -0.0158 0.0490 1.0000
17.250 1.2626 0.10910 0.10315 -0.0190 0.0490 1.0000
17.500 1.2383 0.11688 0.11118 -0.0229 0.0490 1.0000
17.750 1.2131 0.12542 0.11994 -0.0277 0.0492 1.0000
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