WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Reynolds number: 100,000 Max Cl/Cd: 20.42 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx08s176-il-100000-n5.txt Download as CSV file: xf-fx08s176-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 08-S-176 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1087 0.12474 0.11825 -0.0811 0.6495 0.0490
-11.750 -0.1067 0.12170 0.11522 -0.0833 0.6486 0.0492
-11.500 -0.1081 0.11858 0.11215 -0.0861 0.6477 0.0494
-11.250 -0.1064 0.11511 0.10872 -0.0883 0.6466 0.0495
-11.000 -0.0884 0.11005 0.10367 -0.0869 0.6451 0.0505
-10.750 -0.0778 0.10670 0.10032 -0.0871 0.6436 0.0512
-10.500 -0.0735 0.10332 0.09697 -0.0884 0.6424 0.0514
-10.000 -0.0680 0.09452 0.08818 -0.0917 0.6400 0.0369
-9.750 -0.0650 0.09098 0.08466 -0.0928 0.6387 0.0355
-9.500 -0.0649 0.08721 0.08091 -0.0946 0.6377 0.0346
-9.250 -0.0667 0.08324 0.07698 -0.0967 0.6368 0.0343
-9.000 -0.0704 0.07898 0.07276 -0.0993 0.6359 0.0341
-8.750 -0.0778 0.07422 0.06804 -0.1029 0.6350 0.0338
-8.500 -0.0878 0.06999 0.06379 -0.1053 0.6342 0.0342
-8.250 -0.1038 0.06608 0.05987 -0.1058 0.6333 0.0331
-8.000 -0.1197 0.06291 0.05666 -0.1047 0.6322 0.0327
-7.750 -0.1267 0.05997 0.05364 -0.1038 0.6309 0.0329
-7.500 -0.1320 0.05680 0.05032 -0.1025 0.6295 0.0328
-7.250 -0.1351 0.05343 0.04674 -0.1009 0.6280 0.0326
-7.000 -0.1347 0.05011 0.04314 -0.0991 0.6265 0.0323
-6.750 -0.1299 0.04714 0.03988 -0.0973 0.6250 0.0323
-6.500 -0.1217 0.04442 0.03680 -0.0956 0.6237 0.0326
-6.250 -0.1092 0.04235 0.03443 -0.0942 0.6225 0.0337
-6.000 -0.0949 0.04035 0.03205 -0.0927 0.6214 0.0355
-5.750 -0.0788 0.03817 0.02940 -0.0913 0.6204 0.0368
-5.500 -0.0600 0.03614 0.02691 -0.0900 0.6195 0.0374
-5.250 -0.0410 0.03457 0.02500 -0.0888 0.6178 0.0380
-5.000 -0.0207 0.03327 0.02343 -0.0878 0.6159 0.0392
-4.750 0.0000 0.03254 0.02269 -0.0873 0.6139 0.0414
-4.500 0.0226 0.03182 0.02183 -0.0867 0.6121 0.0435
-4.250 0.0466 0.03090 0.02071 -0.0861 0.6105 0.0448
-4.000 0.0711 0.03010 0.01974 -0.0856 0.6092 0.0464
-3.750 0.0957 0.02943 0.01892 -0.0850 0.6079 0.0481
-3.500 0.1198 0.02883 0.01824 -0.0845 0.6067 0.0502
-3.250 0.1431 0.02842 0.01786 -0.0840 0.6056 0.0545
-3.000 0.1644 0.02821 0.01760 -0.0832 0.6040 0.0588
-2.750 0.1804 0.02829 0.01768 -0.0816 0.6012 0.0620
-2.500 0.1969 0.02816 0.01761 -0.0803 0.5990 0.0671
-2.250 0.2158 0.02817 0.01755 -0.0792 0.5971 0.0757
-2.000 0.2353 0.02803 0.01747 -0.0781 0.5954 0.0922
-1.750 0.2559 0.02778 0.01740 -0.0773 0.5938 0.1295
-1.500 0.2633 0.02610 0.01733 -0.0747 0.5924 0.4915
-1.250 0.2656 0.02678 0.01902 -0.0659 0.5912 0.8207
-1.000 0.2752 0.02764 0.01977 -0.0616 0.5894 0.8640
-0.750 0.2715 0.02910 0.02132 -0.0571 0.5848 0.8840
-0.500 0.2932 0.02990 0.02201 -0.0553 0.5820 0.9123
-0.250 0.3289 0.03034 0.02227 -0.0565 0.5801 0.9324
0.000 0.3928 0.03064 0.02232 -0.0632 0.5789 0.9464
0.250 0.4620 0.03071 0.02215 -0.0712 0.5778 0.9547
0.500 0.4871 0.03079 0.02208 -0.0711 0.5765 0.9599
1.000 0.5099 0.03326 0.02459 -0.0699 0.5669 0.9717
1.250 0.5388 0.03342 0.02465 -0.0709 0.5647 0.9748
1.500 0.5726 0.03335 0.02446 -0.0724 0.5632 0.9773
1.750 0.6063 0.03321 0.02419 -0.0736 0.5619 0.9799
2.250 0.6226 0.03610 0.02716 -0.0722 0.5502 0.9916
2.500 0.6539 0.03600 0.02698 -0.0731 0.5486 0.9943
2.750 0.6901 0.03577 0.02667 -0.0748 0.5475 0.9967
3.000 0.7272 0.03561 0.02644 -0.0767 0.5465 0.9996
3.500 0.6455 0.03940 0.03034 -0.0590 0.5324 1.0000
4.500 0.5330 0.04788 0.03888 -0.0378 0.4978 1.0000
4.750 0.5502 0.04844 0.03940 -0.0373 0.4945 1.0000
5.000 0.5741 0.04861 0.03953 -0.0371 0.4927 1.0000
5.250 0.6001 0.04866 0.03954 -0.0372 0.4913 1.0000
5.750 0.6141 0.05156 0.04245 -0.0358 0.4790 1.0000
6.000 0.6112 0.05392 0.04483 -0.0349 0.4703 1.0000
6.250 0.6310 0.05459 0.04549 -0.0350 0.4673 1.0000
6.500 0.6554 0.05489 0.04578 -0.0351 0.4653 1.0000
6.750 0.6814 0.05506 0.04595 -0.0354 0.4640 1.0000
7.250 0.6952 0.05868 0.04964 -0.0348 0.4518 1.0000
8.250 0.7566 0.06340 0.05449 -0.0349 0.4369 1.0000
8.750 0.7650 0.06816 0.05936 -0.0347 0.4253 1.0000
9.000 0.7886 0.06856 0.05980 -0.0349 0.4236 1.0000
9.250 0.8134 0.06885 0.06016 -0.0352 0.4224 1.0000
9.750 0.8152 0.07468 0.06613 -0.0352 0.4105 1.0000
10.000 0.8387 0.07509 0.06661 -0.0354 0.4090 1.0000
10.500 0.8411 0.08107 0.07274 -0.0357 0.3975 1.0000
11.000 0.8766 0.08325 0.07511 -0.0362 0.3926 1.0000
11.500 0.8905 0.08790 0.07995 -0.0367 0.3823 1.0000
11.750 0.9138 0.08824 0.08040 -0.0369 0.3807 1.0000
14.750 1.0715 0.10123 0.09483 -0.0385 0.2781 1.0000
15.000 1.0613 0.10631 0.10004 -0.0397 0.2608 1.0000
15.250 1.0958 0.10270 0.09531 -0.0382 0.1451 1.0000
15.500 1.0723 0.10936 0.10153 -0.0395 0.0959 1.0000
15.750 1.0517 0.11585 0.10763 -0.0410 0.0538 1.0000
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