NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 50,000 Max Cl/Cd: 36.11 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63412-il-50000.txt Download as CSV file: xf-n63412-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-412 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4004 0.11259 0.10539 -0.0196 1.0000 0.3068
-9.500 -0.3910 0.10923 0.10205 -0.0192 1.0000 0.3213
-9.250 -0.3819 0.10592 0.09876 -0.0187 1.0000 0.3356
-9.000 -0.3718 0.10241 0.09527 -0.0184 1.0000 0.3477
-8.750 -0.3679 0.09935 0.09227 -0.0181 1.0000 0.3588
-8.500 -0.3706 0.09697 0.08997 -0.0178 1.0000 0.3708
-8.250 -0.3793 0.09537 0.08849 -0.0170 1.0000 0.3839
-8.000 -0.3581 0.09055 0.08364 -0.0171 1.0000 0.3884
-7.750 -0.3701 0.08883 0.08205 -0.0161 1.0000 0.3997
-7.500 -0.5427 0.06726 0.06088 -0.0462 1.0000 0.1711
-7.250 -0.5587 0.06161 0.05505 -0.0469 1.0000 0.1553
-7.000 -0.5717 0.05627 0.04931 -0.0474 1.0000 0.1445
-6.750 -0.5682 0.05262 0.04537 -0.0466 1.0000 0.1402
-6.500 -0.5622 0.04904 0.04152 -0.0459 1.0000 0.1383
-6.250 -0.5529 0.04549 0.03757 -0.0454 1.0000 0.1364
-6.000 -0.5393 0.04198 0.03354 -0.0452 1.0000 0.1336
-5.750 -0.5219 0.03885 0.02983 -0.0449 1.0000 0.1316
-5.500 -0.5028 0.03639 0.02700 -0.0443 1.0000 0.1330
-5.250 -0.4828 0.03440 0.02468 -0.0437 1.0000 0.1376
-5.000 -0.4606 0.03255 0.02233 -0.0431 1.0000 0.1417
-4.750 -0.4389 0.03067 0.02029 -0.0422 1.0000 0.1458
-4.500 -0.4172 0.02935 0.01884 -0.0413 1.0000 0.1552
-4.250 -0.3964 0.02803 0.01757 -0.0401 1.0000 0.1663
-4.000 -0.3761 0.02686 0.01644 -0.0386 1.0000 0.1798
-3.750 -0.3561 0.02571 0.01541 -0.0374 1.0000 0.2049
-3.500 -0.3350 0.02403 0.01421 -0.0369 1.0000 0.2593
-3.250 -0.3326 0.02274 0.01536 -0.0296 1.0000 0.6237
-3.000 -0.3356 0.02386 0.01652 -0.0210 1.0000 0.6995
-2.750 -0.3369 0.02456 0.01720 -0.0134 1.0000 0.7472
-2.500 -0.3386 0.02499 0.01758 -0.0061 1.0000 0.7873
-2.250 -0.3403 0.02517 0.01771 0.0008 1.0000 0.8280
-2.000 -0.3452 0.02514 0.01763 0.0088 1.0000 0.8734
-1.750 -0.2342 0.02662 0.01858 -0.0006 1.0000 0.9666
-1.500 -0.1356 0.02694 0.01839 -0.0160 1.0000 0.9944
-1.250 -0.1265 0.02664 0.01798 -0.0163 1.0000 1.0000
-1.000 -0.1370 0.02612 0.01742 -0.0133 1.0000 1.0000
-0.750 -0.1468 0.02554 0.01680 -0.0103 1.0000 1.0000
-0.500 -0.1516 0.02503 0.01621 -0.0080 1.0000 1.0000
-0.250 -0.1215 0.02544 0.01641 -0.0117 0.9929 1.0000
0.000 -0.0799 0.02625 0.01700 -0.0172 0.9833 1.0000
0.250 -0.0438 0.02689 0.01747 -0.0213 0.9740 1.0000
0.500 -0.0054 0.02772 0.01811 -0.0257 0.9647 1.0000
0.750 0.0393 0.02881 0.01904 -0.0310 0.9557 1.0000
1.000 0.0693 0.02949 0.01959 -0.0335 0.9462 1.0000
1.250 0.1065 0.03047 0.02046 -0.0372 0.9372 1.0000
1.500 0.1421 0.03144 0.02133 -0.0405 0.9281 1.0000
1.750 0.1718 0.03234 0.02216 -0.0426 0.9188 1.0000
2.000 0.2122 0.03352 0.02328 -0.0464 0.9096 1.0000
2.250 0.2362 0.03437 0.02410 -0.0476 0.8997 1.0000
2.500 0.2666 0.03544 0.02514 -0.0496 0.8900 1.0000
2.750 0.3044 0.03662 0.02632 -0.0527 0.8803 1.0000
3.000 0.3247 0.03758 0.02728 -0.0532 0.8697 1.0000
3.250 0.3538 0.03872 0.02847 -0.0548 0.8595 1.0000
3.500 0.3930 0.03996 0.02974 -0.0578 0.8486 1.0000
3.750 0.4113 0.04101 0.03085 -0.0579 0.8371 1.0000
4.000 0.4356 0.04219 0.03208 -0.0587 0.8250 1.0000
4.250 0.4640 0.04338 0.03338 -0.0600 0.8126 1.0000
4.500 0.4948 0.04457 0.03467 -0.0614 0.7995 1.0000
4.750 0.5264 0.04571 0.03593 -0.0628 0.7855 1.0000
5.000 0.5560 0.04681 0.03719 -0.0638 0.7705 1.0000
5.250 0.5820 0.04789 0.03841 -0.0643 0.7542 1.0000
5.500 0.6072 0.04894 0.03960 -0.0645 0.7367 1.0000
5.750 0.6365 0.04981 0.04066 -0.0648 0.7180 1.0000
6.000 0.6808 0.05001 0.04115 -0.0659 0.6980 1.0000
6.250 0.7088 0.05048 0.04184 -0.0653 0.6757 1.0000
6.500 0.7810 0.04793 0.03979 -0.0661 0.6501 1.0000
6.750 0.8531 0.04301 0.03539 -0.0640 0.6163 1.0000
7.000 0.9637 0.03062 0.02363 -0.0580 0.5556 1.0000
7.250 0.9839 0.02725 0.02023 -0.0508 0.4659 1.0000
7.500 0.9705 0.02825 0.01974 -0.0425 0.2987 1.0000
7.750 0.9648 0.03147 0.02185 -0.0382 0.2228 1.0000
8.000 0.9817 0.03418 0.02405 -0.0366 0.1796 1.0000
8.250 1.0174 0.03673 0.02635 -0.0369 0.1512 1.0000
8.500 1.0649 0.03990 0.02918 -0.0388 0.1330 1.0000
8.750 1.0909 0.04240 0.03207 -0.0382 0.1232 1.0000
9.000 1.1228 0.04600 0.03580 -0.0386 0.1175 1.0000
9.250 1.1390 0.04906 0.03939 -0.0372 0.1134 1.0000
9.500 1.1566 0.05223 0.04283 -0.0363 0.1090 1.0000
9.750 1.1763 0.05619 0.04697 -0.0358 0.1066 1.0000
10.000 1.1859 0.06035 0.05156 -0.0343 0.1063 1.0000
10.250 1.1818 0.06424 0.05602 -0.0318 0.1070 1.0000
10.500 1.1650 0.06834 0.06070 -0.0288 0.1085 1.0000
10.750 1.1427 0.07273 0.06552 -0.0261 0.1102 1.0000
11.000 1.1155 0.07700 0.07005 -0.0237 0.1117 1.0000
11.250 1.0851 0.08189 0.07517 -0.0228 0.1133 1.0000
11.500 1.0556 0.08759 0.08104 -0.0235 0.1150 1.0000
11.750 1.0303 0.09408 0.08764 -0.0254 0.1167 1.0000
12.000 1.0207 0.10056 0.09418 -0.0272 0.1184 1.0000
12.250 0.7231 0.13006 0.12406 -0.0454 0.1538 1.0000
12.500 0.7332 0.13543 0.12948 -0.0461 0.1607 1.0000
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Polar data table (+)
Polar graphs
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