WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 100,000 Max Cl/Cd: 33.2 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77080-il-100000-n5.txt Download as CSV file: xf-fx77080-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7839 0.07482 0.06953 -0.0173 1.0000 0.0278
-10.750 -0.8016 0.06747 0.06212 -0.0233 1.0000 0.0273
-10.500 -0.8246 0.06121 0.05573 -0.0274 1.0000 0.0268
-10.250 -0.8489 0.05647 0.05077 -0.0278 1.0000 0.0269
-10.000 -0.8680 0.05231 0.04631 -0.0264 1.0000 0.0272
-9.750 -0.8784 0.04826 0.04186 -0.0248 1.0000 0.0275
-9.500 -0.8837 0.04447 0.03752 -0.0228 1.0000 0.0281
-9.250 -0.8796 0.04118 0.03402 -0.0213 1.0000 0.0288
-9.000 -0.8704 0.03862 0.03124 -0.0198 1.0000 0.0296
-8.750 -0.8589 0.03627 0.02863 -0.0183 1.0000 0.0305
-8.500 -0.8454 0.03405 0.02607 -0.0168 1.0000 0.0315
-8.250 -0.8300 0.03209 0.02381 -0.0153 1.0000 0.0333
-8.000 -0.8129 0.03031 0.02164 -0.0139 1.0000 0.0359
-7.750 -0.7953 0.02831 0.01940 -0.0125 1.0000 0.0378
-7.500 -0.7768 0.02676 0.01778 -0.0113 1.0000 0.0397
-7.250 -0.7572 0.02545 0.01633 -0.0100 1.0000 0.0425
-7.000 -0.7366 0.02428 0.01490 -0.0087 1.0000 0.0463
-6.750 -0.7175 0.02300 0.01358 -0.0074 1.0000 0.0502
-6.500 -0.6973 0.02195 0.01245 -0.0061 1.0000 0.0545
-6.250 -0.6770 0.02095 0.01136 -0.0048 1.0000 0.0608
-6.000 -0.6563 0.02011 0.01049 -0.0035 1.0000 0.0688
-5.750 -0.6359 0.01926 0.00963 -0.0022 1.0000 0.0785
-5.500 -0.6148 0.01853 0.00892 -0.0010 1.0000 0.0930
-5.250 -0.5934 0.01788 0.00825 0.0003 1.0000 0.1095
-5.000 -0.5719 0.01730 0.00772 0.0014 1.0000 0.1287
-4.750 -0.5502 0.01678 0.00720 0.0025 1.0000 0.1481
-4.500 -0.5282 0.01633 0.00673 0.0036 1.0000 0.1690
-4.250 -0.5067 0.01582 0.00633 0.0048 1.0000 0.1908
-4.000 -0.4850 0.01537 0.00592 0.0059 1.0000 0.2145
-3.750 -0.4636 0.01489 0.00555 0.0071 1.0000 0.2408
-3.500 -0.4423 0.01442 0.00519 0.0083 1.0000 0.2721
-3.250 -0.4214 0.01393 0.00489 0.0097 1.0000 0.3116
-3.000 -0.4008 0.01346 0.00462 0.0110 1.0000 0.3616
-2.750 -0.3805 0.01298 0.00441 0.0125 1.0000 0.4226
-2.500 -0.3605 0.01251 0.00423 0.0142 1.0000 0.4927
-2.250 -0.3399 0.01208 0.00413 0.0158 1.0000 0.5725
-2.000 -0.3172 0.01171 0.00409 0.0173 1.0000 0.6548
-1.750 -0.2922 0.01147 0.00413 0.0185 1.0000 0.7375
-1.500 -0.2608 0.01137 0.00420 0.0185 1.0000 0.8119
-1.250 -0.2187 0.01141 0.00431 0.0163 1.0000 0.8755
-1.000 -0.1713 0.01150 0.00439 0.0128 1.0000 0.9204
-0.750 -0.1175 0.01159 0.00443 0.0078 1.0000 0.9549
-0.500 -0.0602 0.01165 0.00445 0.0019 1.0000 0.9829
-0.250 -0.0117 0.01168 0.00444 -0.0026 1.0000 1.0000
0.000 0.0000 0.01166 0.00442 0.0000 1.0000 1.0000
0.250 0.0118 0.01168 0.00444 0.0026 1.0000 1.0000
0.500 0.0614 0.01165 0.00445 -0.0021 0.9824 1.0000
0.750 0.1178 0.01159 0.00443 -0.0078 0.9547 1.0000
1.000 0.1714 0.01150 0.00438 -0.0128 0.9204 1.0000
1.250 0.2185 0.01141 0.00432 -0.0163 0.8761 1.0000
1.500 0.2602 0.01137 0.00421 -0.0185 0.8140 1.0000
1.750 0.2923 0.01147 0.00412 -0.0185 0.7364 1.0000
2.000 0.3173 0.01172 0.00408 -0.0173 0.6528 1.0000
2.250 0.3398 0.01209 0.00412 -0.0158 0.5710 1.0000
2.500 0.3605 0.01251 0.00423 -0.0142 0.4929 1.0000
2.750 0.3806 0.01297 0.00441 -0.0125 0.4234 1.0000
3.000 0.4007 0.01346 0.00462 -0.0110 0.3607 1.0000
3.250 0.4214 0.01394 0.00489 -0.0096 0.3113 1.0000
3.500 0.4423 0.01442 0.00519 -0.0083 0.2719 1.0000
3.750 0.4636 0.01490 0.00555 -0.0071 0.2405 1.0000
4.000 0.4850 0.01537 0.00592 -0.0059 0.2143 1.0000
4.250 0.5067 0.01582 0.00633 -0.0048 0.1907 1.0000
4.500 0.5282 0.01633 0.00674 -0.0036 0.1693 1.0000
4.750 0.5502 0.01679 0.00721 -0.0025 0.1486 1.0000
5.000 0.5719 0.01731 0.00773 -0.0014 0.1289 1.0000
5.250 0.5934 0.01788 0.00826 -0.0002 0.1097 1.0000
5.500 0.6149 0.01852 0.00891 0.0010 0.0926 1.0000
5.750 0.6359 0.01924 0.00961 0.0022 0.0781 1.0000
6.000 0.6563 0.02011 0.01049 0.0035 0.0688 1.0000
6.250 0.6769 0.02095 0.01137 0.0048 0.0607 1.0000
6.500 0.6973 0.02195 0.01245 0.0061 0.0544 1.0000
6.750 0.7175 0.02299 0.01358 0.0074 0.0501 1.0000
7.000 0.7367 0.02426 0.01490 0.0087 0.0461 1.0000
7.250 0.7572 0.02545 0.01633 0.0100 0.0422 1.0000
7.500 0.7768 0.02676 0.01777 0.0113 0.0396 1.0000
7.750 0.7952 0.02833 0.01942 0.0125 0.0377 1.0000
8.000 0.8128 0.03030 0.02167 0.0139 0.0355 1.0000
8.250 0.8299 0.03211 0.02384 0.0154 0.0333 1.0000
8.500 0.8454 0.03403 0.02606 0.0168 0.0315 1.0000
8.750 0.8590 0.03625 0.02859 0.0183 0.0303 1.0000
9.000 0.8706 0.03858 0.03118 0.0198 0.0295 1.0000
9.250 0.8794 0.04124 0.03407 0.0213 0.0287 1.0000
9.500 0.8829 0.04456 0.03765 0.0229 0.0280 1.0000
9.750 0.8795 0.04826 0.04182 0.0247 0.0277 1.0000
10.000 0.8679 0.05236 0.04636 0.0264 0.0272 1.0000
10.250 0.8500 0.05644 0.05073 0.0278 0.0270 1.0000
10.500 0.8264 0.06110 0.05560 0.0275 0.0270 1.0000
10.750 0.8054 0.06691 0.06153 0.0239 0.0274 1.0000
11.000 0.7808 0.07583 0.07056 0.0161 0.0277 1.0000
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