NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 100,000 Max Cl/Cd: 52.98 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651412-il-100000.txt Download as CSV file: xf-naca651412-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4187 0.09531 0.09040 -0.0462 1.0000 0.1221
-9.250 -0.4491 0.09178 0.08705 -0.0503 1.0000 0.1257
-9.000 -0.4840 0.08843 0.08386 -0.0527 1.0000 0.1261
-8.750 -0.4399 0.08610 0.08147 -0.0463 1.0000 0.1364
-8.500 -0.4676 0.08335 0.07887 -0.0462 1.0000 0.1385
-8.250 -0.4966 0.08129 0.07695 -0.0437 1.0000 0.1383
-8.000 -0.5279 0.07959 0.07536 -0.0404 1.0000 0.1379
-7.750 -0.5599 0.07751 0.07332 -0.0382 1.0000 0.1387
-7.500 -0.5999 0.07559 0.07132 -0.0370 1.0000 0.1404
-7.250 -0.6076 0.07194 0.06772 -0.0350 1.0000 0.1437
-7.000 -0.6006 0.07009 0.06594 -0.0319 1.0000 0.1503
-6.750 -0.6271 0.06678 0.06239 -0.0324 1.0000 0.1577
-6.500 -0.6164 0.06476 0.06051 -0.0293 1.0000 0.1666
-6.000 -0.5851 0.05792 0.05353 -0.0331 0.9913 0.2074
-5.250 -0.4736 0.03763 0.02968 -0.0465 0.9751 0.0832
-5.000 -0.4391 0.03427 0.02599 -0.0486 0.9716 0.0821
-4.750 -0.4081 0.03165 0.02306 -0.0496 0.9674 0.0799
-4.500 -0.3762 0.02967 0.02074 -0.0503 0.9625 0.0785
-4.250 -0.3393 0.02813 0.01887 -0.0519 0.9584 0.0795
-4.000 -0.3051 0.02726 0.01771 -0.0531 0.9539 0.0829
-3.750 -0.2781 0.02593 0.01635 -0.0530 0.9488 0.0850
-3.500 -0.2451 0.02482 0.01536 -0.0542 0.9444 0.0892
-3.250 -0.2072 0.02414 0.01464 -0.0563 0.9410 0.0985
-3.000 -0.1882 0.02344 0.01407 -0.0552 0.9341 0.1072
-2.750 -0.1559 0.02275 0.01341 -0.0565 0.9296 0.1275
-2.500 -0.1366 0.02042 0.01382 -0.0546 0.9265 0.6949
-2.250 -0.1330 0.02116 0.01463 -0.0482 0.9186 0.7586
-2.000 -0.1227 0.02202 0.01552 -0.0421 0.9130 0.8079
-1.750 -0.1224 0.02262 0.01612 -0.0351 0.9063 0.8436
-1.500 -0.1226 0.02309 0.01660 -0.0273 0.8999 0.8802
-1.250 -0.1010 0.02364 0.01708 -0.0227 0.8964 0.9258
-1.000 -0.0720 0.02383 0.01713 -0.0232 0.8910 0.9464
-0.750 -0.0241 0.02398 0.01710 -0.0280 0.8869 0.9526
-0.500 0.0221 0.02410 0.01706 -0.0324 0.8833 0.9599
-0.250 0.0814 0.02428 0.01710 -0.0393 0.8813 0.9638
0.000 0.1123 0.02450 0.01726 -0.0416 0.8748 0.9727
0.250 0.1657 0.02467 0.01734 -0.0476 0.8711 0.9775
0.500 0.2180 0.02480 0.01741 -0.0533 0.8681 0.9832
0.750 0.2713 0.02495 0.01752 -0.0592 0.8651 0.9881
1.000 0.3053 0.02529 0.01786 -0.0623 0.8586 0.9980
1.250 0.3351 0.02544 0.01801 -0.0639 0.8537 1.0000
1.500 0.3140 0.02584 0.01840 -0.0571 0.8439 1.0000
1.750 0.3315 0.02601 0.01856 -0.0563 0.8384 1.0000
2.000 0.3191 0.02644 0.01897 -0.0511 0.8291 1.0000
2.250 0.3504 0.02672 0.01926 -0.0527 0.8240 1.0000
2.500 0.3707 0.02724 0.01978 -0.0527 0.8170 1.0000
2.750 0.3996 0.02764 0.02022 -0.0539 0.8104 1.0000
3.000 0.4452 0.02779 0.02042 -0.0572 0.8068 1.0000
3.250 0.4548 0.02861 0.02126 -0.0557 0.7965 1.0000
3.500 0.4992 0.02872 0.02147 -0.0586 0.7925 1.0000
3.750 0.5118 0.02957 0.02235 -0.0575 0.7821 1.0000
4.000 0.5605 0.02941 0.02232 -0.0605 0.7775 1.0000
4.250 0.5802 0.02989 0.02289 -0.0598 0.7657 1.0000
4.500 0.6110 0.03003 0.02317 -0.0603 0.7558 1.0000
4.750 0.6605 0.02940 0.02274 -0.0628 0.7493 1.0000
5.000 0.7603 0.02391 0.01760 -0.0667 0.7304 1.0000
5.250 0.8277 0.01875 0.01252 -0.0657 0.6899 1.0000
5.500 0.8562 0.01748 0.01137 -0.0636 0.6553 1.0000
5.750 0.8720 0.01646 0.01029 -0.0592 0.5776 1.0000
6.000 0.8524 0.01827 0.01015 -0.0502 0.2672 1.0000
6.250 0.8386 0.02126 0.01188 -0.0446 0.1258 1.0000
6.500 0.8446 0.02284 0.01324 -0.0415 0.1022 1.0000
6.750 0.8531 0.02430 0.01460 -0.0388 0.0915 1.0000
7.000 0.8680 0.02559 0.01585 -0.0370 0.0825 1.0000
7.250 0.8902 0.02718 0.01740 -0.0363 0.0760 1.0000
7.500 0.9240 0.02890 0.01910 -0.0371 0.0711 1.0000
7.750 0.9717 0.03191 0.02194 -0.0402 0.0664 1.0000
8.000 1.0008 0.03352 0.02385 -0.0402 0.0635 1.0000
8.250 1.0343 0.03603 0.02662 -0.0408 0.0623 1.0000
8.500 1.0632 0.03889 0.02983 -0.0408 0.0621 1.0000
8.750 1.0875 0.04212 0.03345 -0.0401 0.0629 1.0000
9.000 1.1065 0.04551 0.03724 -0.0389 0.0635 1.0000
9.250 1.1200 0.04883 0.04099 -0.0372 0.0636 1.0000
9.500 1.1305 0.05251 0.04504 -0.0354 0.0642 1.0000
9.750 1.1533 0.05894 0.05156 -0.0358 0.0672 1.0000
10.000 1.0904 0.05766 0.05151 -0.0267 0.0799 1.0000
12.000 0.8292 0.13212 0.12757 -0.0484 0.1680 1.0000
12.250 0.6746 0.13382 0.12968 -0.0425 0.1670 1.0000
12.500 0.6939 0.13715 0.13304 -0.0416 0.1636 1.0000
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Polar data table (+)
Polar graphs
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