FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 100,000 Max Cl/Cd: 41.74 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74modsm-il-100000.txt Download as CSV file: xf-fx74modsm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-Cl5-140 MOD (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-9.250 0.1944 0.10914 0.10454 -0.1208 0.8841 0.0404
-9.000 0.2101 0.10850 0.10381 -0.1272 0.8710 0.0409
-8.750 0.2242 0.10760 0.10283 -0.1327 0.8574 0.0411
-8.500 0.2509 0.09897 0.09413 -0.1318 0.8470 0.0422
-8.250 0.2693 0.09514 0.09020 -0.1329 0.8352 0.0434
-8.000 0.2849 0.09244 0.08740 -0.1346 0.8241 0.0448
-7.750 0.2975 0.09023 0.08512 -0.1359 0.8127 0.0462
-7.500 0.3076 0.08836 0.08321 -0.1369 0.8016 0.0477
-7.250 0.3191 0.08654 0.08131 -0.1384 0.7922 0.0493
-7.000 0.3269 0.08551 0.08026 -0.1400 0.7822 0.0508
-6.750 0.3289 0.08586 0.08062 -0.1418 0.7726 0.0517
-6.500 0.3399 0.08604 0.08076 -0.1473 0.7645 0.0522
-6.250 0.3497 0.08389 0.07865 -0.1494 0.7562 0.0527
-6.000 0.3608 0.07828 0.07297 -0.1433 0.7503 0.0544
-5.750 0.3725 0.07600 0.07067 -0.1427 0.7434 0.0565
-5.500 0.3833 0.07428 0.06895 -0.1434 0.7361 0.0592
-5.250 0.3996 0.07268 0.06727 -0.1467 0.7304 0.0630
-5.000 0.4316 0.07339 0.06800 -0.1626 0.7219 0.0659
-4.750 0.4359 0.06920 0.06379 -0.1576 0.7174 0.0673
-4.500 0.4402 0.06707 0.06170 -0.1535 0.7113 0.0694
-4.250 0.4540 0.06522 0.05984 -0.1540 0.7050 0.0729
-3.750 0.5172 0.06064 0.05517 -0.1714 0.6932 0.0826
-3.500 0.5237 0.05874 0.05328 -0.1673 0.6883 0.0857
-3.250 0.5918 0.05497 0.04922 -0.1857 0.6841 0.0983
-3.000 0.5861 0.05409 0.04851 -0.1795 0.6773 0.1006
-2.750 0.6349 0.05115 0.04540 -0.1897 0.6721 0.1155
-2.500 0.6725 0.04864 0.04274 -0.1945 0.6684 0.1329
-2.250 0.6958 0.04742 0.04156 -0.1974 0.6617 0.1491
-2.000 0.7435 0.04538 0.03934 -0.2052 0.6567 0.1805
-1.750 0.7800 0.04347 0.03730 -0.2084 0.6531 0.2137
-0.750 0.9906 0.03501 0.02773 -0.2379 0.6327 0.2015
-0.500 1.0601 0.03253 0.02403 -0.2452 0.6276 0.1048
-0.250 1.1006 0.03191 0.02282 -0.2471 0.6237 0.0979
0.000 1.1365 0.03147 0.02206 -0.2484 0.6203 0.0970
0.250 1.1534 0.03193 0.02260 -0.2471 0.6143 0.0964
0.500 1.1829 0.03175 0.02231 -0.2475 0.6101 0.0972
0.750 1.2176 0.03122 0.02179 -0.2487 0.6068 0.1058
1.000 1.2406 0.03180 0.02238 -0.2483 0.6021 0.1149
1.250 1.2628 0.03249 0.02313 -0.2480 0.5967 0.1330
1.500 1.2864 0.03135 0.02363 -0.2468 0.5935 0.8630
1.750 1.3144 0.03149 0.02338 -0.2464 0.5906 1.0000
2.000 1.3256 0.03314 0.02501 -0.2445 0.5852 1.0000
2.250 1.3431 0.03431 0.02609 -0.2434 0.5801 1.0000
2.500 1.3740 0.03458 0.02614 -0.2440 0.5769 1.0000
2.750 1.4079 0.03477 0.02609 -0.2450 0.5743 1.0000
3.000 1.3964 0.03796 0.02952 -0.2404 0.5675 1.0000
3.250 1.4148 0.03904 0.03054 -0.2394 0.5632 1.0000
3.500 1.4493 0.03901 0.03033 -0.2404 0.5605 1.0000
3.750 1.4871 0.03886 0.02999 -0.2418 0.5583 1.0000
4.000 1.2787 0.05807 0.05026 -0.2186 0.5375 1.0000
4.250 1.3460 0.05447 0.04639 -0.2211 0.5381 1.0000
4.500 1.4269 0.05053 0.04217 -0.2260 0.5391 1.0000
4.750 1.5417 0.04465 0.03583 -0.2357 0.5421 1.0000
5.000 1.3740 0.06052 0.05234 -0.2166 0.5261 1.0000
5.250 1.4385 0.05733 0.04899 -0.2191 0.5263 1.0000
5.500 1.5144 0.05389 0.04535 -0.2237 0.5267 1.0000
5.750 1.0244 0.11760 0.11079 -0.2105 0.5136 1.0000
6.000 1.0423 0.11768 0.11072 -0.2089 0.4994 1.0000
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Polar data table (+)
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