NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 50,000 Max Cl/Cd: 23.5 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf414f-il-50000-n5.txt Download as CSV file: xf-nlf414f-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4030 0.09924 0.09206 -0.0814 0.9659 0.0496
-10.250 -0.4075 0.09555 0.08838 -0.0823 0.9642 0.0492
-10.000 -0.4158 0.09168 0.08452 -0.0834 0.9624 0.0488
-9.750 -0.4285 0.08799 0.08082 -0.0840 0.9609 0.0484
-9.500 -0.4452 0.08469 0.07751 -0.0838 0.9595 0.0480
-9.250 -0.4647 0.08173 0.07450 -0.0828 0.9578 0.0476
-9.000 -0.4915 0.07991 0.07268 -0.0790 0.9551 0.0472
-8.750 -0.5138 0.07760 0.07031 -0.0758 0.9530 0.0468
-8.500 -0.5319 0.07498 0.06761 -0.0730 0.9512 0.0466
-8.250 -0.5448 0.07207 0.06451 -0.0708 0.9490 0.0464
-8.000 -0.5532 0.06904 0.06127 -0.0689 0.9471 0.0463
-7.750 -0.5584 0.06608 0.05806 -0.0670 0.9457 0.0464
-7.500 -0.5580 0.06301 0.05468 -0.0656 0.9443 0.0466
-7.250 -0.5579 0.06026 0.05161 -0.0635 0.9424 0.0468
-7.000 -0.5555 0.05763 0.04865 -0.0612 0.9407 0.0470
-6.750 -0.5489 0.05500 0.04565 -0.0593 0.9393 0.0472
-6.500 -0.5378 0.05241 0.04266 -0.0579 0.9377 0.0472
-6.250 -0.5224 0.04994 0.03980 -0.0569 0.9360 0.0473
-6.000 -0.5037 0.04765 0.03708 -0.0562 0.9345 0.0475
-5.750 -0.4827 0.04559 0.03462 -0.0556 0.9332 0.0480
-5.500 -0.4595 0.04377 0.03240 -0.0551 0.9321 0.0487
-5.250 -0.4340 0.04220 0.03049 -0.0549 0.9308 0.0501
-5.000 -0.4080 0.04096 0.02920 -0.0551 0.9295 0.0530
-4.750 -0.3854 0.03996 0.02805 -0.0543 0.9280 0.0559
-4.500 -0.3638 0.03906 0.02695 -0.0528 0.9265 0.0584
-4.250 -0.3418 0.03824 0.02605 -0.0513 0.9251 0.0609
-4.000 -0.3210 0.03760 0.02538 -0.0500 0.9233 0.0659
-3.750 -0.2992 0.03704 0.02467 -0.0488 0.9213 0.0720
-3.500 -0.2780 0.03634 0.02400 -0.0480 0.9194 0.0799
-3.250 -0.2555 0.03567 0.02332 -0.0476 0.9176 0.0927
-3.000 -0.2313 0.03483 0.02263 -0.0477 0.9157 0.1188
-2.750 -0.2155 0.03189 0.02210 -0.0477 0.9143 0.4486
-2.250 -0.2235 0.03441 0.02527 -0.0289 0.9077 0.8032
-2.000 -0.2266 0.03489 0.02574 -0.0187 0.9048 0.8610
-1.750 -0.1546 0.03586 0.02633 -0.0216 0.9055 0.9391
-1.500 -0.1186 0.03600 0.02617 -0.0241 0.9031 0.9450
-1.250 -0.0817 0.03622 0.02611 -0.0268 0.9008 0.9505
-1.000 -0.0543 0.03638 0.02608 -0.0278 0.8980 0.9566
-0.750 -0.0242 0.03651 0.02604 -0.0295 0.8944 0.9610
-0.500 0.0046 0.03671 0.02608 -0.0309 0.8909 0.9658
-0.250 0.0326 0.03698 0.02620 -0.0321 0.8876 0.9702
0.000 0.0689 0.03738 0.02647 -0.0348 0.8847 0.9730
0.250 0.0886 0.03755 0.02657 -0.0346 0.8798 0.9771
0.500 0.1128 0.03784 0.02678 -0.0351 0.8752 0.9808
0.750 0.1428 0.03825 0.02712 -0.0366 0.8714 0.9840
1.000 0.1676 0.03861 0.02742 -0.0373 0.8664 0.9872
1.250 0.1890 0.03892 0.02771 -0.0373 0.8606 0.9909
1.750 0.2383 0.03974 0.02850 -0.0384 0.8496 0.9976
2.000 0.2594 0.04012 0.02888 -0.0382 0.8434 1.0000
2.250 0.2762 0.04049 0.02925 -0.0371 0.8374 1.0000
2.500 0.2838 0.04069 0.02948 -0.0344 0.8293 1.0000
2.750 0.3111 0.04121 0.03002 -0.0350 0.8246 1.0000
3.250 0.3391 0.04180 0.03068 -0.0317 0.8094 1.0000
3.750 0.3754 0.04251 0.03150 -0.0299 0.7939 1.0000
4.000 0.3841 0.04277 0.03183 -0.0278 0.7831 1.0000
4.250 0.4138 0.04326 0.03240 -0.0288 0.7768 1.0000
4.500 0.4310 0.04360 0.03284 -0.0280 0.7665 1.0000
4.750 0.4534 0.04397 0.03332 -0.0280 0.7571 1.0000
5.000 0.4846 0.04430 0.03377 -0.0291 0.7493 1.0000
5.250 0.5041 0.04459 0.03419 -0.0286 0.7379 1.0000
5.500 0.5277 0.04482 0.03459 -0.0287 0.7270 1.0000
5.750 0.5546 0.04488 0.03481 -0.0289 0.7155 1.0000
6.000 0.5830 0.04435 0.03444 -0.0288 0.6997 1.0000
6.250 0.6175 0.04308 0.03338 -0.0286 0.6815 1.0000
6.500 0.6420 0.04211 0.03258 -0.0273 0.6599 1.0000
6.750 0.6700 0.04110 0.03178 -0.0265 0.6391 1.0000
7.000 0.6976 0.03999 0.03089 -0.0254 0.6160 1.0000
7.250 0.7233 0.03873 0.02986 -0.0238 0.5873 1.0000
7.500 0.7424 0.03803 0.02934 -0.0218 0.5456 1.0000
7.750 0.7814 0.03548 0.02670 -0.0199 0.4653 1.0000
8.000 0.8105 0.03449 0.02458 -0.0171 0.3141 1.0000
8.250 0.8132 0.03642 0.02584 -0.0149 0.2374 1.0000
8.500 0.8192 0.03837 0.02737 -0.0134 0.1916 1.0000
8.750 0.8292 0.04013 0.02887 -0.0123 0.1624 1.0000
9.000 0.8426 0.04171 0.03034 -0.0114 0.1412 1.0000
9.250 0.8591 0.04313 0.03169 -0.0107 0.1258 1.0000
9.500 0.8788 0.04439 0.03294 -0.0102 0.1135 1.0000
9.750 0.9027 0.04551 0.03405 -0.0099 0.1043 1.0000
10.000 0.9303 0.04651 0.03512 -0.0099 0.0955 1.0000
10.250 0.9664 0.04744 0.03617 -0.0103 0.0884 1.0000
10.500 1.0001 0.04863 0.03748 -0.0108 0.0828 1.0000
10.750 1.0334 0.05016 0.03908 -0.0115 0.0780 1.0000
11.000 1.0628 0.05209 0.04133 -0.0118 0.0740 1.0000
11.250 1.0901 0.05424 0.04371 -0.0121 0.0714 1.0000
11.500 1.1137 0.05642 0.04599 -0.0124 0.0690 1.0000
11.750 1.1279 0.05919 0.04905 -0.0119 0.0669 1.0000
12.000 1.1318 0.06221 0.05252 -0.0106 0.0652 1.0000
12.250 1.1329 0.06541 0.05610 -0.0093 0.0639 1.0000
12.500 1.1306 0.06889 0.05992 -0.0080 0.0630 1.0000
12.750 1.1236 0.07264 0.06400 -0.0067 0.0625 1.0000
13.000 1.1119 0.07671 0.06841 -0.0056 0.0621 1.0000
13.250 1.0956 0.08120 0.07320 -0.0047 0.0619 1.0000
13.500 1.0745 0.08627 0.07856 -0.0043 0.0618 1.0000
13.750 1.0484 0.09215 0.08471 -0.0049 0.0619 1.0000
14.000 1.0165 0.09927 0.09209 -0.0067 0.0622 1.0000
14.250 0.9784 0.10838 0.10143 -0.0108 0.0628 1.0000
14.500 0.9361 0.12047 0.11369 -0.0180 0.0636 1.0000
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Polar data table (+)
Polar graphs
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