GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 200,000 Max Cl/Cd: 77.96 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe796-il-200000.txt Download as CSV file: xf-goe796-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3883 0.10042 0.09684 -0.0481 1.0000 0.0709
-9.250 -0.4102 0.09747 0.09398 -0.0484 1.0000 0.0711
-9.000 -0.4333 0.09514 0.09174 -0.0470 1.0000 0.0711
-8.750 -0.4220 0.09128 0.08790 -0.0434 1.0000 0.0719
-8.500 -0.4267 0.08956 0.08624 -0.0402 1.0000 0.0723
-8.250 -0.4414 0.08818 0.08492 -0.0367 1.0000 0.0726
-8.000 -0.4545 0.08650 0.08332 -0.0344 0.9991 0.0730
-7.750 -0.4826 0.05592 0.05227 -0.0656 0.9847 0.0509
-7.500 -0.4764 0.04519 0.04103 -0.0718 0.9766 0.0466
-7.250 -0.4703 0.03257 0.02713 -0.0767 0.9710 0.0442
-7.000 -0.4466 0.02953 0.02361 -0.0776 0.9634 0.0448
-6.750 -0.4130 0.02697 0.02061 -0.0799 0.9597 0.0458
-6.500 -0.3756 0.02471 0.01793 -0.0825 0.9575 0.0466
-6.250 -0.3487 0.02314 0.01606 -0.0826 0.9495 0.0475
-6.000 -0.3109 0.02170 0.01434 -0.0848 0.9462 0.0488
-5.750 -0.2719 0.01997 0.01246 -0.0873 0.9441 0.0514
-5.500 -0.2417 0.01915 0.01163 -0.0880 0.9373 0.0550
-5.250 -0.2077 0.01805 0.01046 -0.0892 0.9324 0.0632
-5.000 -0.1697 0.01764 0.01007 -0.0912 0.9291 0.0769
-4.750 -0.1405 0.01750 0.00986 -0.0914 0.9215 0.0862
-4.500 -0.1070 0.01742 0.00969 -0.0924 0.9160 0.0944
-4.250 -0.0722 0.01698 0.00923 -0.0938 0.9124 0.1015
-4.000 -0.0471 0.01679 0.00899 -0.0932 0.9034 0.1076
-3.750 -0.0155 0.01634 0.00851 -0.0938 0.8986 0.1158
-3.500 0.0116 0.01616 0.00830 -0.0936 0.8911 0.1248
-3.250 0.0400 0.01562 0.00778 -0.0936 0.8850 0.1337
-3.000 0.0692 0.01523 0.00736 -0.0936 0.8797 0.1450
-2.750 0.0950 0.01499 0.00713 -0.0932 0.8717 0.1574
-2.500 0.1243 0.01457 0.00674 -0.0933 0.8669 0.1705
-2.250 0.1494 0.01431 0.00654 -0.0927 0.8581 0.1820
-2.000 0.1780 0.01394 0.00618 -0.0925 0.8522 0.1956
-1.750 0.2035 0.01369 0.00598 -0.0919 0.8432 0.2108
-1.500 0.2316 0.01331 0.00566 -0.0917 0.8370 0.2338
-1.250 0.2563 0.01294 0.00553 -0.0911 0.8281 0.2793
-1.000 0.2804 0.01207 0.00530 -0.0904 0.8218 0.4392
-0.750 0.2941 0.01097 0.00544 -0.0868 0.8131 0.7702
-0.500 0.3737 0.01069 0.00534 -0.0959 0.8075 0.9867
-0.250 0.4190 0.01067 0.00519 -0.0996 0.7990 1.0000
0.000 0.4446 0.01067 0.00506 -0.0990 0.7920 1.0000
0.250 0.4690 0.01075 0.00505 -0.0983 0.7842 1.0000
0.500 0.4947 0.01079 0.00498 -0.0978 0.7773 1.0000
0.750 0.5194 0.01088 0.00500 -0.0971 0.7696 1.0000
1.000 0.5450 0.01094 0.00496 -0.0965 0.7621 1.0000
1.250 0.5699 0.01103 0.00500 -0.0958 0.7541 1.0000
1.500 0.5956 0.01111 0.00500 -0.0953 0.7465 1.0000
1.750 0.6205 0.01122 0.00507 -0.0946 0.7385 1.0000
2.000 0.6463 0.01130 0.00507 -0.0940 0.7303 1.0000
2.250 0.6707 0.01141 0.00515 -0.0932 0.7208 1.0000
2.500 0.6970 0.01147 0.00512 -0.0926 0.7120 1.0000
2.750 0.7210 0.01156 0.00520 -0.0917 0.7009 1.0000
3.000 0.7459 0.01165 0.00527 -0.0910 0.6906 1.0000
3.250 0.7722 0.01173 0.00526 -0.0904 0.6812 1.0000
3.500 0.7962 0.01182 0.00537 -0.0895 0.6693 1.0000
3.750 0.8208 0.01191 0.00546 -0.0888 0.6575 1.0000
4.000 0.8458 0.01199 0.00551 -0.0880 0.6455 1.0000
4.250 0.8707 0.01207 0.00555 -0.0872 0.6324 1.0000
4.500 0.8950 0.01215 0.00561 -0.0864 0.6176 1.0000
4.750 0.9187 0.01225 0.00571 -0.0854 0.6010 1.0000
5.000 0.9422 0.01237 0.00582 -0.0844 0.5829 1.0000
5.250 0.9655 0.01253 0.00594 -0.0834 0.5635 1.0000
5.500 0.9883 0.01272 0.00606 -0.0823 0.5423 1.0000
5.750 1.0103 0.01296 0.00625 -0.0812 0.5189 1.0000
6.000 1.0322 0.01327 0.00646 -0.0800 0.4972 1.0000
6.250 1.0538 0.01361 0.00672 -0.0788 0.4757 1.0000
6.500 1.0745 0.01400 0.00703 -0.0775 0.4538 1.0000
6.750 1.0947 0.01443 0.00735 -0.0761 0.4326 1.0000
7.000 1.1151 0.01485 0.00772 -0.0749 0.4138 1.0000
7.250 1.1357 0.01530 0.00812 -0.0736 0.3973 1.0000
7.500 1.1559 0.01576 0.00856 -0.0724 0.3818 1.0000
7.750 1.1758 0.01623 0.00901 -0.0711 0.3668 1.0000
8.000 1.1950 0.01672 0.00949 -0.0697 0.3515 1.0000
8.250 1.2130 0.01723 0.00999 -0.0681 0.3348 1.0000
8.500 1.2295 0.01777 0.01053 -0.0663 0.3165 1.0000
8.750 1.2442 0.01836 0.01108 -0.0642 0.2969 1.0000
9.000 1.2579 0.01892 0.01164 -0.0620 0.2748 1.0000
9.250 1.2681 0.01954 0.01221 -0.0592 0.2519 1.0000
9.500 1.2778 0.02025 0.01287 -0.0564 0.2289 1.0000
9.750 1.2856 0.02115 0.01367 -0.0536 0.2087 1.0000
10.000 1.2931 0.02218 0.01460 -0.0509 0.1920 1.0000
10.250 1.3000 0.02334 0.01567 -0.0483 0.1782 1.0000
10.500 1.3079 0.02450 0.01681 -0.0459 0.1658 1.0000
10.750 1.3175 0.02560 0.01794 -0.0439 0.1543 1.0000
11.000 1.3264 0.02678 0.01914 -0.0419 0.1439 1.0000
11.250 1.3331 0.02812 0.02046 -0.0399 0.1344 1.0000
11.500 1.3451 0.02914 0.02160 -0.0385 0.1243 1.0000
11.750 1.3543 0.03040 0.02291 -0.0369 0.1155 1.0000
12.000 1.3604 0.03191 0.02440 -0.0352 0.1073 1.0000
12.250 1.3698 0.03325 0.02582 -0.0339 0.0983 1.0000
12.500 1.3752 0.03494 0.02755 -0.0324 0.0899 1.0000
12.750 1.3757 0.03711 0.02968 -0.0308 0.0819 1.0000
13.000 1.3786 0.03918 0.03185 -0.0295 0.0730 1.0000
13.250 1.3776 0.04168 0.03440 -0.0281 0.0647 1.0000
13.500 1.3713 0.04474 0.03745 -0.0267 0.0585 1.0000
13.750 1.3711 0.04734 0.04015 -0.0258 0.0524 1.0000
14.000 1.3649 0.05058 0.04340 -0.0247 0.0483 1.0000
14.250 1.3655 0.05327 0.04621 -0.0241 0.0441 1.0000
14.500 1.3596 0.05669 0.04963 -0.0236 0.0413 1.0000
14.750 1.3581 0.05974 0.05280 -0.0232 0.0387 1.0000
15.000 1.3569 0.06286 0.05602 -0.0230 0.0364 1.0000
15.250 1.3534 0.06630 0.05951 -0.0230 0.0347 1.0000
15.500 1.3474 0.06992 0.06314 -0.0227 0.0332 1.0000
15.750 1.3465 0.07322 0.06663 -0.0228 0.0319 1.0000
16.000 1.3446 0.07667 0.07021 -0.0230 0.0306 1.0000
16.250 1.3423 0.08023 0.07386 -0.0235 0.0294 1.0000
16.500 1.3392 0.08388 0.07755 -0.0240 0.0284 1.0000
16.750 1.3369 0.08707 0.08072 -0.0236 0.0272 1.0000
17.000 1.3337 0.09105 0.08489 -0.0245 0.0265 1.0000
17.250 1.3301 0.09507 0.08908 -0.0254 0.0258 1.0000
17.500 1.3266 0.09907 0.09323 -0.0263 0.0251 1.0000
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Polar data table (+)
Polar graphs
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