WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 100,000 Max Cl/Cd: 57.32 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx80080-il-100000.txt Download as CSV file: xf-fx80080-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
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 -0.4536 0.09295 0.08816 -0.0353 1.0000 0.0829
-8.000 -0.4701 0.09044 0.08579 -0.0386 1.0000 0.0836
-7.750 -0.4843 0.08739 0.08282 -0.0440 1.0000 0.0841
-7.500 -0.4718 0.08234 0.07783 -0.0389 1.0000 0.0864
-7.250 -0.4661 0.07959 0.07513 -0.0361 1.0000 0.0899
-7.000 -0.4715 0.07656 0.07215 -0.0366 1.0000 0.0929
-6.750 -0.4819 0.07380 0.06940 -0.0380 1.0000 0.0959
-6.500 -0.5037 0.07290 0.06812 -0.0415 1.0000 0.0981
-6.250 -0.4946 0.06743 0.06301 -0.0369 1.0000 0.1007
-6.000 -0.4922 0.06499 0.06059 -0.0346 1.0000 0.1045
-5.750 -0.4942 0.06191 0.05714 -0.0378 1.0000 0.1129
-5.500 -0.4874 0.05853 0.05396 -0.0346 1.0000 0.1164
-5.250 -0.4798 0.05542 0.05056 -0.0361 1.0000 0.1275
-5.000 -0.4693 0.05284 0.04796 -0.0349 1.0000 0.1378
-4.750 -0.4583 0.04984 0.04473 -0.0355 1.0000 0.1552
-4.500 -0.4479 0.04701 0.04202 -0.0337 1.0000 0.1721
-3.750 -0.3621 0.03409 0.02739 -0.0381 1.0000 0.1163
-3.500 -0.3201 0.02847 0.02048 -0.0375 1.0000 0.0670
-3.250 -0.2933 0.02599 0.01749 -0.0371 1.0000 0.0644
-3.000 -0.2679 0.02442 0.01551 -0.0363 1.0000 0.0675
-2.750 -0.2426 0.02318 0.01386 -0.0354 1.0000 0.0710
-2.500 -0.2180 0.02138 0.01203 -0.0348 1.0000 0.0746
-2.250 -0.1941 0.02039 0.01094 -0.0340 1.0000 0.0823
-2.000 -0.1709 0.01951 0.01008 -0.0332 1.0000 0.0984
-1.750 -0.1476 0.01839 0.00914 -0.0326 1.0000 0.1277
-1.500 -0.1327 0.01536 0.00904 -0.0294 1.0000 0.7477
-1.250 -0.1164 0.01481 0.00874 -0.0252 1.0000 1.0000
-1.000 -0.0930 0.01501 0.00861 -0.0252 1.0000 1.0000
-0.750 -0.0697 0.01525 0.00858 -0.0252 1.0000 1.0000
-0.500 -0.0466 0.01552 0.00859 -0.0252 1.0000 1.0000
-0.250 -0.0237 0.01582 0.00869 -0.0252 1.0000 1.0000
0.000 0.0116 0.01633 0.00901 -0.0276 0.9963 1.0000
0.250 0.0485 0.01682 0.00934 -0.0303 0.9907 1.0000
0.500 0.0846 0.01732 0.00969 -0.0328 0.9850 1.0000
0.750 0.1223 0.01786 0.01012 -0.0355 0.9791 1.0000
1.000 0.1561 0.01831 0.01050 -0.0376 0.9726 1.0000
1.250 0.1944 0.01885 0.01098 -0.0404 0.9663 1.0000
1.500 0.2274 0.01928 0.01138 -0.0422 0.9585 1.0000
1.750 0.2696 0.01983 0.01191 -0.0456 0.9517 1.0000
2.000 0.3006 0.02020 0.01230 -0.0469 0.9424 1.0000
2.250 0.3394 0.02067 0.01283 -0.0496 0.9346 1.0000
2.500 0.3792 0.02104 0.01326 -0.0524 0.9252 1.0000
2.750 0.4142 0.02135 0.01365 -0.0541 0.9139 1.0000
3.000 0.4531 0.02161 0.01401 -0.0564 0.9025 1.0000
3.250 0.4965 0.02169 0.01428 -0.0591 0.8899 1.0000
3.500 0.5453 0.02144 0.01422 -0.0623 0.8749 1.0000
3.750 0.6149 0.02023 0.01330 -0.0678 0.8570 1.0000
4.000 0.6793 0.01862 0.01206 -0.0716 0.8355 1.0000
4.250 0.7350 0.01693 0.01067 -0.0735 0.8118 1.0000
4.500 0.7659 0.01590 0.00986 -0.0714 0.7791 1.0000
4.750 0.7936 0.01484 0.00900 -0.0687 0.7308 1.0000
5.000 0.8128 0.01418 0.00823 -0.0643 0.6125 1.0000
5.250 0.8072 0.01657 0.00839 -0.0570 0.2742 1.0000
5.500 0.8109 0.01905 0.00981 -0.0532 0.1612 1.0000
5.750 0.8248 0.02081 0.01121 -0.0509 0.1204 1.0000
6.000 0.8446 0.02252 0.01283 -0.0493 0.0975 1.0000
6.250 0.8676 0.02461 0.01469 -0.0487 0.0804 1.0000
6.500 0.8964 0.02660 0.01694 -0.0482 0.0714 1.0000
6.750 0.9245 0.02912 0.01961 -0.0480 0.0631 1.0000
7.000 0.9508 0.03151 0.02220 -0.0474 0.0572 1.0000
7.250 0.9760 0.03601 0.02695 -0.0470 0.0541 1.0000
7.500 0.9924 0.03791 0.02954 -0.0443 0.0502 1.0000
7.750 1.0078 0.04168 0.03387 -0.0420 0.0496 1.0000
8.000 1.0188 0.04610 0.03882 -0.0394 0.0507 1.0000
8.250 1.0270 0.05099 0.04410 -0.0370 0.0525 1.0000
10.750 0.7777 0.10688 0.10294 -0.0255 0.1338 1.0000
11.000 0.7358 0.11418 0.11018 -0.0330 0.1334 1.0000
11.250 0.7081 0.11997 0.11587 -0.0381 0.1326 1.0000
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Polar data table (+)
Polar graphs
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