WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 100,000 Max Cl/Cd: 33.67 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77080-il-100000.txt Download as CSV file: xf-fx77080-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6460 0.09155 0.08647 0.0015 1.0000 0.1489
-8.750 -0.7860 0.05941 0.05377 -0.0219 1.0000 0.0702
-8.500 -0.7853 0.05455 0.04876 -0.0211 1.0000 0.0687
-8.250 -0.7872 0.04939 0.04328 -0.0199 1.0000 0.0673
-8.000 -0.7871 0.04427 0.03769 -0.0181 1.0000 0.0664
-7.750 -0.7817 0.04008 0.03299 -0.0161 1.0000 0.0671
-7.500 -0.7722 0.03665 0.02897 -0.0140 1.0000 0.0692
-7.250 -0.7595 0.03367 0.02529 -0.0117 1.0000 0.0710
-7.000 -0.7430 0.03027 0.02159 -0.0101 1.0000 0.0730
-6.750 -0.7229 0.02844 0.01967 -0.0089 1.0000 0.0773
-6.500 -0.7028 0.02688 0.01767 -0.0072 1.0000 0.0835
-6.250 -0.6812 0.02487 0.01566 -0.0061 1.0000 0.0895
-6.000 -0.6592 0.02349 0.01396 -0.0047 1.0000 0.0981
-5.750 -0.6373 0.02225 0.01272 -0.0035 1.0000 0.1095
-5.500 -0.6155 0.02105 0.01147 -0.0022 1.0000 0.1244
-5.250 -0.5943 0.01982 0.01037 -0.0009 1.0000 0.1436
-5.000 -0.5733 0.01881 0.00935 0.0005 1.0000 0.1694
-4.750 -0.5527 0.01793 0.00855 0.0019 1.0000 0.1979
-4.500 -0.5319 0.01713 0.00790 0.0032 1.0000 0.2260
-4.250 -0.5111 0.01643 0.00732 0.0046 1.0000 0.2552
-4.000 -0.4901 0.01575 0.00677 0.0059 1.0000 0.2867
-3.750 -0.4697 0.01500 0.00628 0.0074 1.0000 0.3222
-3.500 -0.4501 0.01422 0.00579 0.0091 1.0000 0.3712
-3.250 -0.4323 0.01334 0.00540 0.0112 1.0000 0.4476
-3.000 -0.4169 0.01243 0.00517 0.0141 1.0000 0.5675
-2.750 -0.3976 0.01181 0.00517 0.0171 1.0000 0.7042
-2.500 -0.3657 0.01170 0.00534 0.0182 1.0000 0.8199
-2.250 -0.3166 0.01197 0.00557 0.0157 1.0000 0.8976
-2.000 -0.2499 0.01236 0.00574 0.0093 1.0000 0.9439
-1.750 -0.1705 0.01261 0.00572 -0.0003 1.0000 0.9723
-1.500 -0.0868 0.01250 0.00540 -0.0115 1.0000 0.9954
-1.250 -0.0600 0.01224 0.00506 -0.0123 1.0000 1.0000
-1.000 -0.0479 0.01202 0.00482 -0.0101 1.0000 1.0000
-0.750 -0.0358 0.01186 0.00464 -0.0077 1.0000 1.0000
-0.500 -0.0237 0.01175 0.00451 -0.0052 1.0000 1.0000
-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 0.0237 0.01175 0.00451 0.0052 1.0000 1.0000
0.750 0.0359 0.01186 0.00464 0.0077 1.0000 1.0000
1.000 0.0480 0.01202 0.00482 0.0101 1.0000 1.0000
1.250 0.0601 0.01224 0.00506 0.0123 1.0000 1.0000
1.500 0.0868 0.01250 0.00539 0.0115 0.9955 1.0000
1.750 0.1703 0.01261 0.00572 0.0004 0.9724 1.0000
2.000 0.2500 0.01236 0.00574 -0.0093 0.9437 1.0000
2.250 0.3168 0.01196 0.00556 -0.0157 0.8966 1.0000
2.500 0.3658 0.01170 0.00534 -0.0182 0.8198 1.0000
2.750 0.3976 0.01181 0.00517 -0.0171 0.7044 1.0000
3.000 0.4168 0.01244 0.00517 -0.0141 0.5659 1.0000
3.250 0.4323 0.01334 0.00540 -0.0112 0.4472 1.0000
3.500 0.4500 0.01423 0.00580 -0.0090 0.3707 1.0000
3.750 0.4696 0.01500 0.00628 -0.0074 0.3218 1.0000
4.000 0.4900 0.01574 0.00677 -0.0059 0.2864 1.0000
4.250 0.5111 0.01644 0.00733 -0.0046 0.2551 1.0000
4.500 0.5320 0.01715 0.00791 -0.0032 0.2263 1.0000
4.750 0.5528 0.01794 0.00856 -0.0019 0.1981 1.0000
5.000 0.5733 0.01881 0.00936 -0.0005 0.1697 1.0000
5.250 0.5943 0.01982 0.01037 0.0009 0.1437 1.0000
5.500 0.6154 0.02099 0.01143 0.0022 0.1239 1.0000
5.750 0.6374 0.02226 0.01273 0.0035 0.1096 1.0000
6.000 0.6592 0.02349 0.01397 0.0047 0.0982 1.0000
6.250 0.6812 0.02487 0.01566 0.0062 0.0893 1.0000
6.500 0.7026 0.02684 0.01765 0.0073 0.0833 1.0000
6.750 0.7229 0.02836 0.01956 0.0089 0.0769 1.0000
7.000 0.7430 0.03028 0.02158 0.0101 0.0728 1.0000
7.250 0.7593 0.03367 0.02531 0.0117 0.0709 1.0000
7.500 0.7721 0.03664 0.02898 0.0140 0.0690 1.0000
7.750 0.7816 0.04006 0.03298 0.0161 0.0668 1.0000
8.000 0.7866 0.04437 0.03781 0.0182 0.0660 1.0000
8.250 0.7872 0.04941 0.04329 0.0199 0.0673 1.0000
8.500 0.7852 0.05459 0.04880 0.0211 0.0687 1.0000
8.750 0.7851 0.05954 0.05390 0.0219 0.0701 1.0000
9.000 0.6363 0.05597 0.05121 0.0234 0.0785 1.0000
9.250 0.6029 0.06538 0.06065 0.0179 0.0868 1.0000
9.500 0.6121 0.06798 0.06325 0.0198 0.0853 1.0000
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Polar data table (+)
Polar graphs
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