WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 200,000 Max Cl/Cd: 74.73 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx80080-il-200000-n5.txt Download as CSV file: xf-fx80080-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4468 0.09484 0.09123 -0.0311 1.0000 0.0159
-8.750 -0.4477 0.09076 0.08720 -0.0325 1.0000 0.0151
-8.500 -0.4492 0.08688 0.08337 -0.0340 1.0000 0.0149
-8.250 -0.4529 0.08294 0.07949 -0.0354 1.0000 0.0142
-8.000 -0.4598 0.07915 0.07577 -0.0365 1.0000 0.0136
-7.750 -0.4705 0.07581 0.07253 -0.0372 1.0000 0.0139
-7.500 -0.4803 0.07112 0.06790 -0.0401 1.0000 0.0133
-7.250 -0.4843 0.06250 0.05922 -0.0469 0.9961 0.0119
-7.000 -0.4630 0.05880 0.05542 -0.0519 0.9898 0.0129
-6.750 -0.4412 0.05426 0.05072 -0.0569 0.9821 0.0143
-6.500 -0.4182 0.04826 0.04445 -0.0619 0.9745 0.0157
-6.250 -0.3946 0.04208 0.03791 -0.0659 0.9679 0.0149
-6.000 -0.3704 0.03609 0.03147 -0.0685 0.9616 0.0144
-5.750 -0.3441 0.03053 0.02534 -0.0703 0.9561 0.0140
-5.500 -0.3139 0.02589 0.02006 -0.0720 0.9529 0.0138
-5.250 -0.2859 0.02270 0.01632 -0.0725 0.9476 0.0141
-5.000 -0.2552 0.02029 0.01345 -0.0734 0.9437 0.0149
-4.750 -0.2227 0.01840 0.01119 -0.0744 0.9409 0.0158
-4.500 -0.1889 0.01731 0.00981 -0.0758 0.9386 0.0179
-4.250 -0.1611 0.01606 0.00836 -0.0759 0.9334 0.0195
-4.000 -0.1312 0.01475 0.00695 -0.0765 0.9295 0.0209
-3.750 -0.0989 0.01390 0.00603 -0.0777 0.9264 0.0233
-3.500 -0.0686 0.01324 0.00527 -0.0784 0.9222 0.0265
-3.250 -0.0397 0.01269 0.00468 -0.0788 0.9174 0.0347
-3.000 -0.0086 0.01216 0.00408 -0.0797 0.9138 0.0483
-2.750 0.0232 0.01169 0.00369 -0.0808 0.9106 0.0808
-2.500 0.0487 0.01114 0.00344 -0.0808 0.9049 0.1566
-2.250 0.0754 0.01024 0.00320 -0.0813 0.9004 0.3433
-2.000 0.0967 0.00923 0.00325 -0.0803 0.8963 0.6301
-1.750 0.1191 0.00916 0.00336 -0.0787 0.8906 0.7323
-1.500 0.1458 0.00918 0.00338 -0.0781 0.8865 0.7758
-1.250 0.1728 0.00920 0.00339 -0.0776 0.8830 0.8060
-1.000 0.1934 0.00926 0.00349 -0.0755 0.8775 0.8415
-0.750 0.2153 0.00926 0.00351 -0.0736 0.8732 0.8720
-0.500 0.2423 0.00925 0.00346 -0.0732 0.8699 0.8870
-0.250 0.2663 0.00926 0.00346 -0.0723 0.8645 0.8965
0.000 0.2942 0.00925 0.00342 -0.0723 0.8601 0.9036
0.250 0.3240 0.00925 0.00339 -0.0727 0.8565 0.9111
0.500 0.3506 0.00927 0.00341 -0.0725 0.8510 0.9180
0.750 0.3797 0.00928 0.00341 -0.0729 0.8462 0.9256
1.000 0.4116 0.00927 0.00340 -0.0737 0.8415 0.9324
1.250 0.4405 0.00928 0.00344 -0.0740 0.8342 0.9412
1.500 0.4745 0.00927 0.00345 -0.0752 0.8283 0.9490
1.750 0.5067 0.00926 0.00349 -0.0762 0.8190 0.9586
2.000 0.5405 0.00923 0.00349 -0.0774 0.8078 0.9693
2.250 0.5743 0.00916 0.00343 -0.0786 0.7925 0.9832
2.500 0.6040 0.00912 0.00342 -0.0788 0.7743 1.0000
2.750 0.6260 0.00913 0.00344 -0.0775 0.7532 1.0000
3.000 0.6500 0.00915 0.00344 -0.0765 0.7302 1.0000
3.250 0.6735 0.00921 0.00348 -0.0755 0.7008 1.0000
3.500 0.6965 0.00932 0.00351 -0.0743 0.6568 1.0000
3.750 0.7136 0.00975 0.00353 -0.0717 0.5550 1.0000
4.000 0.7233 0.01074 0.00384 -0.0682 0.4258 1.0000
4.250 0.7347 0.01182 0.00434 -0.0654 0.3077 1.0000
4.500 0.7509 0.01271 0.00484 -0.0636 0.2238 1.0000
4.750 0.7686 0.01357 0.00537 -0.0621 0.1546 1.0000
5.000 0.7870 0.01442 0.00592 -0.0608 0.1010 1.0000
5.250 0.8075 0.01510 0.00646 -0.0597 0.0717 1.0000
5.500 0.8290 0.01569 0.00709 -0.0588 0.0560 1.0000
5.750 0.8502 0.01633 0.00775 -0.0577 0.0448 1.0000
6.000 0.8703 0.01712 0.00855 -0.0565 0.0366 1.0000
6.250 0.8911 0.01782 0.00932 -0.0554 0.0303 1.0000
6.500 0.9096 0.01881 0.01036 -0.0539 0.0261 1.0000
6.750 0.9294 0.01971 0.01141 -0.0525 0.0237 1.0000
7.000 0.9497 0.02055 0.01235 -0.0514 0.0204 1.0000
7.250 0.9669 0.02194 0.01383 -0.0499 0.0171 1.0000
7.500 0.9887 0.02263 0.01469 -0.0490 0.0142 1.0000
7.750 1.0091 0.02343 0.01557 -0.0480 0.0115 1.0000
8.000 1.0242 0.02582 0.01812 -0.0462 0.0099 1.0000
8.250 1.0439 0.02756 0.02013 -0.0450 0.0092 1.0000
8.500 1.0623 0.02977 0.02266 -0.0436 0.0086 1.0000
8.750 1.0782 0.03238 0.02565 -0.0419 0.0080 1.0000
9.000 1.0903 0.03533 0.02901 -0.0398 0.0077 1.0000
9.250 1.0975 0.03862 0.03274 -0.0371 0.0075 1.0000
9.500 1.0992 0.04218 0.03673 -0.0340 0.0074 1.0000
9.750 1.0947 0.04596 0.04093 -0.0305 0.0073 1.0000
10.000 1.0831 0.04959 0.04491 -0.0263 0.0073 1.0000
10.250 1.0677 0.05321 0.04883 -0.0224 0.0072 1.0000
10.500 1.0487 0.05726 0.05316 -0.0193 0.0073 1.0000
10.750 1.0277 0.06174 0.05788 -0.0175 0.0074 1.0000
11.000 1.0064 0.06666 0.06300 -0.0170 0.0074 1.0000
11.250 0.9825 0.07262 0.06915 -0.0182 0.0075 1.0000
11.500 0.9594 0.07949 0.07618 -0.0214 0.0076 1.0000
11.750 0.9357 0.08846 0.08529 -0.0272 0.0078 1.0000
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Polar data table (+)
Polar graphs
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