WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 500,000 Max Cl/Cd: 90.46 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx80080-il-500000-n5.txt Download as CSV file: xf-fx80080-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4656 0.10050 0.09815 -0.0266 1.0000 0.0060
-9.500 -0.4651 0.09644 0.09411 -0.0282 1.0000 0.0059
-9.250 -0.4643 0.09260 0.09030 -0.0297 1.0000 0.0057
-9.000 -0.4645 0.08855 0.08628 -0.0314 1.0000 0.0057
-8.750 -0.4671 0.08416 0.08192 -0.0332 1.0000 0.0057
-8.500 -0.4717 0.07973 0.07754 -0.0350 1.0000 0.0058
-8.250 -0.4788 0.07602 0.07388 -0.0362 1.0000 0.0057
-8.000 -0.4905 0.07297 0.07089 -0.0365 1.0000 0.0056
-7.750 -0.4761 0.06296 0.06082 -0.0512 0.9854 0.0057
-7.500 -0.4611 0.05456 0.05230 -0.0604 0.9720 0.0057
-7.250 -0.4419 0.04535 0.04281 -0.0684 0.9610 0.0058
-7.000 -0.4179 0.03522 0.03220 -0.0745 0.9530 0.0061
-6.750 -0.3943 0.02444 0.02052 -0.0788 0.9444 0.0064
-6.500 -0.3604 0.02296 0.01879 -0.0819 0.9393 0.0073
-6.250 -0.3288 0.02025 0.01567 -0.0839 0.9320 0.0076
-6.000 -0.2966 0.01717 0.01208 -0.0857 0.9252 0.0078
-5.750 -0.2668 0.01522 0.00976 -0.0865 0.9173 0.0080
-5.500 -0.2358 0.01385 0.00813 -0.0875 0.9109 0.0084
-5.250 -0.2081 0.01285 0.00693 -0.0877 0.9035 0.0089
-4.750 -0.1525 0.01143 0.00519 -0.0880 0.8909 0.0103
-4.500 -0.1248 0.01095 0.00460 -0.0881 0.8851 0.0108
-4.250 -0.0993 0.01030 0.00383 -0.0878 0.8793 0.0118
-4.000 -0.0730 0.00985 0.00333 -0.0877 0.8737 0.0139
-3.750 -0.0457 0.00955 0.00295 -0.0877 0.8693 0.0159
-3.500 -0.0195 0.00928 0.00261 -0.0874 0.8645 0.0178
-3.250 0.0072 0.00899 0.00227 -0.0872 0.8599 0.0240
-3.000 0.0344 0.00879 0.00205 -0.0872 0.8558 0.0346
-2.750 0.0604 0.00858 0.00190 -0.0869 0.8509 0.0534
-2.500 0.0870 0.00839 0.00175 -0.0868 0.8464 0.0758
-2.000 0.1380 0.00763 0.00149 -0.0864 0.8382 0.2391
-1.750 0.1628 0.00720 0.00139 -0.0862 0.8341 0.3529
-1.500 0.1866 0.00664 0.00129 -0.0857 0.8303 0.5118
-1.250 0.2090 0.00620 0.00136 -0.0847 0.8266 0.6713
-1.000 0.2344 0.00613 0.00141 -0.0841 0.8225 0.7224
-0.750 0.2607 0.00612 0.00144 -0.0837 0.8185 0.7506
-0.500 0.2873 0.00615 0.00147 -0.0833 0.8149 0.7769
-0.250 0.3125 0.00615 0.00154 -0.0826 0.8101 0.8026
0.000 0.3384 0.00617 0.00158 -0.0820 0.8050 0.8181
0.250 0.3651 0.00619 0.00159 -0.0817 0.7993 0.8270
0.500 0.3914 0.00619 0.00159 -0.0813 0.7921 0.8327
0.750 0.4179 0.00621 0.00160 -0.0810 0.7848 0.8381
1.250 0.4701 0.00622 0.00162 -0.0801 0.7641 0.8472
1.500 0.4954 0.00624 0.00161 -0.0795 0.7489 0.8520
1.750 0.5207 0.00629 0.00161 -0.0789 0.7316 0.8571
2.000 0.5458 0.00632 0.00164 -0.0782 0.7140 0.8619
2.250 0.5697 0.00641 0.00166 -0.0773 0.6842 0.8677
2.500 0.5925 0.00655 0.00173 -0.0761 0.6462 0.8735
2.750 0.6113 0.00689 0.00181 -0.0741 0.5755 0.8806
3.000 0.6236 0.00770 0.00208 -0.0711 0.4501 0.8888
3.250 0.6408 0.00836 0.00237 -0.0692 0.3578 0.8977
3.500 0.6602 0.00888 0.00264 -0.0677 0.2871 0.9082
3.750 0.6793 0.00947 0.00294 -0.0662 0.2103 0.9225
4.000 0.7020 0.01007 0.00329 -0.0656 0.1401 0.9430
4.250 0.7354 0.01059 0.00364 -0.0673 0.0956 0.9744
4.500 0.7600 0.01098 0.00393 -0.0669 0.0736 1.0000
4.750 0.7838 0.01133 0.00423 -0.0663 0.0584 1.0000
5.000 0.8076 0.01168 0.00455 -0.0657 0.0467 1.0000
5.250 0.8311 0.01206 0.00493 -0.0650 0.0363 1.0000
5.500 0.8541 0.01249 0.00532 -0.0643 0.0268 1.0000
5.750 0.8777 0.01286 0.00572 -0.0636 0.0225 1.0000
6.000 0.8998 0.01338 0.00625 -0.0627 0.0178 1.0000
6.250 0.9232 0.01376 0.00668 -0.0620 0.0158 1.0000
6.500 0.9461 0.01417 0.00712 -0.0613 0.0135 1.0000
6.750 0.9677 0.01474 0.00770 -0.0603 0.0107 1.0000
7.000 0.9898 0.01524 0.00831 -0.0594 0.0092 1.0000
7.250 1.0117 0.01576 0.00891 -0.0585 0.0079 1.0000
7.500 1.0325 0.01640 0.00957 -0.0575 0.0060 1.0000
7.750 1.0516 0.01730 0.01058 -0.0560 0.0051 1.0000
8.000 1.0711 0.01812 0.01152 -0.0547 0.0046 1.0000
8.250 1.0912 0.01884 0.01233 -0.0536 0.0041 1.0000
8.500 1.1117 0.01949 0.01305 -0.0526 0.0037 1.0000
8.750 1.1311 0.02027 0.01390 -0.0515 0.0033 1.0000
9.000 1.1456 0.02174 0.01554 -0.0495 0.0029 1.0000
9.250 1.1628 0.02281 0.01679 -0.0480 0.0028 1.0000
9.500 1.1787 0.02406 0.01823 -0.0463 0.0027 1.0000
9.750 1.1930 0.02549 0.01986 -0.0445 0.0026 1.0000
10.000 1.2066 0.02690 0.02148 -0.0426 0.0025 1.0000
10.250 1.2167 0.02859 0.02341 -0.0402 0.0024 1.0000
10.500 1.2237 0.03043 0.02551 -0.0374 0.0023 1.0000
10.750 1.2269 0.03253 0.02788 -0.0343 0.0023 1.0000
11.000 1.2274 0.03472 0.03034 -0.0310 0.0022 1.0000
11.250 1.2247 0.03710 0.03298 -0.0276 0.0021 1.0000
11.500 1.2162 0.04001 0.03619 -0.0242 0.0021 1.0000
11.750 1.2054 0.04316 0.03961 -0.0212 0.0020 1.0000
12.000 1.1873 0.04721 0.04396 -0.0185 0.0020 1.0000
12.250 1.1732 0.05101 0.04799 -0.0170 0.0019 1.0000
12.500 1.1568 0.05536 0.05256 -0.0163 0.0019 1.0000
12.750 1.1224 0.06276 0.06025 -0.0172 0.0020 1.0000
13.000 1.1028 0.06893 0.06659 -0.0196 0.0019 1.0000
13.250 1.0773 0.07754 0.07538 -0.0247 0.0020 1.0000
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Polar data table (+)
Polar graphs
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