GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 200,000 Max Cl/Cd: 73.25 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe796-il-200000-n5.txt Download as CSV file: xf-goe796-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4050 0.11368 0.10971 -0.0392 1.0000 0.0269
-11.250 -0.4048 0.10950 0.10554 -0.0408 1.0000 0.0267
-10.250 -0.7010 0.04280 0.03846 -0.0739 0.9946 0.0240
-10.000 -0.6953 0.03719 0.03230 -0.0775 0.9877 0.0241
-9.750 -0.6762 0.03374 0.02843 -0.0798 0.9834 0.0242
-9.500 -0.6561 0.03124 0.02560 -0.0809 0.9781 0.0244
-9.250 -0.6313 0.02912 0.02319 -0.0823 0.9740 0.0246
-9.000 -0.6027 0.02727 0.02105 -0.0841 0.9712 0.0249
-8.750 -0.5785 0.02584 0.01940 -0.0844 0.9655 0.0252
-8.500 -0.5504 0.02455 0.01791 -0.0854 0.9611 0.0257
-8.250 -0.5199 0.02334 0.01649 -0.0867 0.9580 0.0263
-8.000 -0.4951 0.02233 0.01530 -0.0867 0.9514 0.0268
-7.750 -0.4666 0.02133 0.01413 -0.0873 0.9465 0.0272
-7.500 -0.4358 0.02039 0.01303 -0.0883 0.9429 0.0276
-7.250 -0.4122 0.01963 0.01217 -0.0877 0.9350 0.0281
-7.000 -0.3832 0.01888 0.01133 -0.0882 0.9298 0.0288
-6.750 -0.3562 0.01827 0.01063 -0.0882 0.9234 0.0296
-6.500 -0.3292 0.01769 0.00997 -0.0882 0.9164 0.0307
-6.250 -0.3001 0.01711 0.00929 -0.0885 0.9112 0.0323
-6.000 -0.2748 0.01661 0.00872 -0.0880 0.9025 0.0343
-5.750 -0.2459 0.01612 0.00818 -0.0882 0.8968 0.0383
-5.500 -0.2202 0.01570 0.00772 -0.0877 0.8878 0.0435
-5.250 -0.1915 0.01532 0.00723 -0.0878 0.8816 0.0500
-5.000 -0.1655 0.01497 0.00687 -0.0874 0.8724 0.0559
-4.750 -0.1374 0.01465 0.00648 -0.0874 0.8656 0.0617
-4.500 -0.1106 0.01440 0.00623 -0.0872 0.8566 0.0681
-4.250 -0.0828 0.01416 0.00595 -0.0871 0.8493 0.0736
-4.000 -0.0554 0.01398 0.00574 -0.0869 0.8405 0.0806
-3.750 -0.0276 0.01382 0.00556 -0.0868 0.8327 0.0892
-3.500 0.0001 0.01367 0.00535 -0.0867 0.8247 0.0974
-3.250 0.0276 0.01348 0.00513 -0.0866 0.8170 0.1047
-3.000 0.0553 0.01333 0.00491 -0.0864 0.8091 0.1122
-2.750 0.0826 0.01313 0.00471 -0.0863 0.8018 0.1212
-2.500 0.1102 0.01298 0.00452 -0.0862 0.7943 0.1295
-2.250 0.1375 0.01281 0.00433 -0.0860 0.7866 0.1379
-2.000 0.1649 0.01266 0.00415 -0.0859 0.7782 0.1462
-1.750 0.1922 0.01252 0.00400 -0.0857 0.7695 0.1562
-1.500 0.2195 0.01238 0.00385 -0.0855 0.7610 0.1687
-1.250 0.2466 0.01225 0.00376 -0.0853 0.7523 0.1865
-1.000 0.2738 0.01208 0.00365 -0.0852 0.7447 0.2159
-0.750 0.3004 0.01188 0.00360 -0.0850 0.7361 0.2615
-0.500 0.3267 0.01162 0.00353 -0.0847 0.7284 0.3315
-0.250 0.3511 0.01119 0.00352 -0.0842 0.7188 0.4510
0.000 0.3736 0.01067 0.00352 -0.0830 0.7108 0.6151
0.250 0.3955 0.01023 0.00362 -0.0812 0.7031 0.7843
0.500 0.4440 0.01012 0.00370 -0.0847 0.6972 0.9364
0.750 0.4842 0.01019 0.00373 -0.0873 0.6899 0.9764
1.000 0.5264 0.01027 0.00372 -0.0904 0.6828 0.9964
1.250 0.5560 0.01034 0.00374 -0.0908 0.6750 1.0000
1.500 0.5812 0.01043 0.00376 -0.0902 0.6675 1.0000
1.750 0.6064 0.01052 0.00381 -0.0896 0.6598 1.0000
2.000 0.6315 0.01062 0.00384 -0.0890 0.6517 1.0000
2.250 0.6564 0.01071 0.00390 -0.0884 0.6421 1.0000
2.500 0.6812 0.01081 0.00395 -0.0877 0.6318 1.0000
2.750 0.7059 0.01092 0.00400 -0.0870 0.6201 1.0000
3.000 0.7305 0.01103 0.00409 -0.0863 0.6079 1.0000
3.250 0.7552 0.01115 0.00418 -0.0856 0.5954 1.0000
3.500 0.7799 0.01128 0.00427 -0.0849 0.5822 1.0000
3.750 0.8042 0.01143 0.00437 -0.0842 0.5673 1.0000
4.000 0.8284 0.01159 0.00449 -0.0834 0.5507 1.0000
4.250 0.8522 0.01178 0.00462 -0.0826 0.5323 1.0000
4.500 0.8753 0.01200 0.00476 -0.0816 0.5115 1.0000
4.750 0.8980 0.01226 0.00494 -0.0807 0.4883 1.0000
5.250 0.9422 0.01288 0.00538 -0.0785 0.4447 1.0000
5.500 0.9639 0.01324 0.00564 -0.0774 0.4249 1.0000
5.750 0.9848 0.01364 0.00595 -0.0762 0.4053 1.0000
6.000 1.0062 0.01403 0.00628 -0.0751 0.3893 1.0000
6.250 1.0278 0.01440 0.00661 -0.0741 0.3753 1.0000
6.500 1.0487 0.01482 0.00698 -0.0730 0.3601 1.0000
6.750 1.0686 0.01528 0.00738 -0.0717 0.3432 1.0000
7.000 1.0883 0.01574 0.00778 -0.0704 0.3270 1.0000
7.250 1.1090 0.01615 0.00819 -0.0692 0.3134 1.0000
7.500 1.1294 0.01655 0.00860 -0.0681 0.3004 1.0000
7.750 1.1494 0.01697 0.00905 -0.0669 0.2871 1.0000
8.000 1.1688 0.01741 0.00950 -0.0656 0.2726 1.0000
8.250 1.1870 0.01788 0.00997 -0.0641 0.2546 1.0000
8.500 1.2027 0.01845 0.01048 -0.0622 0.2317 1.0000
8.750 1.2142 0.01915 0.01108 -0.0597 0.2067 1.0000
9.000 1.2245 0.01995 0.01177 -0.0571 0.1872 1.0000
9.250 1.2352 0.02079 0.01255 -0.0547 0.1732 1.0000
9.500 1.2462 0.02167 0.01339 -0.0525 0.1619 1.0000
9.750 1.2578 0.02255 0.01426 -0.0504 0.1514 1.0000
10.000 1.2711 0.02336 0.01512 -0.0487 0.1411 1.0000
10.250 1.2832 0.02425 0.01603 -0.0469 0.1308 1.0000
10.500 1.2950 0.02520 0.01697 -0.0451 0.1198 1.0000
10.750 1.3070 0.02616 0.01794 -0.0435 0.1083 1.0000
11.000 1.3178 0.02723 0.01901 -0.0418 0.0974 1.0000
11.250 1.3275 0.02840 0.02019 -0.0402 0.0885 1.0000
11.500 1.3360 0.02970 0.02150 -0.0385 0.0812 1.0000
11.750 1.3455 0.03097 0.02282 -0.0370 0.0750 1.0000
12.000 1.3529 0.03244 0.02432 -0.0355 0.0696 1.0000
12.250 1.3617 0.03384 0.02581 -0.0342 0.0641 1.0000
12.500 1.3675 0.03553 0.02754 -0.0328 0.0588 1.0000
12.750 1.3749 0.03714 0.02923 -0.0316 0.0531 1.0000
13.000 1.3796 0.03903 0.03119 -0.0304 0.0480 1.0000
13.250 1.3843 0.04097 0.03319 -0.0293 0.0425 1.0000
13.500 1.3874 0.04311 0.03540 -0.0283 0.0379 1.0000
13.750 1.3886 0.04551 0.03784 -0.0274 0.0339 1.0000
14.000 1.3897 0.04797 0.04039 -0.0266 0.0308 1.0000
14.250 1.3885 0.05074 0.04322 -0.0259 0.0282 1.0000
14.500 1.3868 0.05368 0.04626 -0.0254 0.0262 1.0000
14.750 1.3850 0.05672 0.04940 -0.0251 0.0245 1.0000
15.000 1.3810 0.06011 0.05288 -0.0249 0.0231 1.0000
15.250 1.3746 0.06392 0.05680 -0.0250 0.0220 1.0000
15.500 1.3710 0.06751 0.06054 -0.0253 0.0211 1.0000
15.750 1.3657 0.07141 0.06457 -0.0257 0.0202 1.0000
16.000 1.3593 0.07559 0.06888 -0.0264 0.0194 1.0000
16.250 1.3515 0.08011 0.07353 -0.0274 0.0188 1.0000
16.500 1.3419 0.08502 0.07857 -0.0286 0.0183 1.0000
16.750 1.3305 0.09035 0.08401 -0.0302 0.0179 1.0000
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