NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 100,000 Max Cl/Cd: 39.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca641112-il-100000-n5.txt Download as CSV file: xf-naca641112-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6717 0.08614 0.08095 -0.0256 1.0000 0.0319
-11.250 -0.6957 0.07784 0.07260 -0.0314 1.0000 0.0314
-11.000 -0.7207 0.07104 0.06568 -0.0358 1.0000 0.0311
-10.750 -0.7428 0.06567 0.06015 -0.0383 1.0000 0.0308
-10.500 -0.7628 0.06134 0.05564 -0.0392 1.0000 0.0309
-10.250 -0.7807 0.05768 0.05180 -0.0385 1.0000 0.0309
-10.000 -0.7943 0.05432 0.04820 -0.0369 1.0000 0.0310
-9.750 -0.8010 0.05083 0.04441 -0.0355 1.0000 0.0311
-9.500 -0.8028 0.04741 0.04065 -0.0341 1.0000 0.0312
-9.250 -0.7999 0.04418 0.03703 -0.0326 1.0000 0.0315
-9.000 -0.7924 0.04119 0.03365 -0.0312 1.0000 0.0319
-8.750 -0.7813 0.03843 0.03047 -0.0299 1.0000 0.0324
-8.500 -0.7672 0.03606 0.02769 -0.0287 1.0000 0.0332
-8.250 -0.7511 0.03400 0.02528 -0.0275 1.0000 0.0343
-8.000 -0.7328 0.03204 0.02327 -0.0269 1.0000 0.0357
-7.750 -0.7135 0.03046 0.02156 -0.0261 1.0000 0.0369
-7.500 -0.6933 0.02888 0.01982 -0.0251 1.0000 0.0380
-7.250 -0.6732 0.02745 0.01826 -0.0241 1.0000 0.0392
-7.000 -0.6540 0.02616 0.01686 -0.0228 1.0000 0.0406
-6.750 -0.6364 0.02513 0.01571 -0.0213 1.0000 0.0426
-6.500 -0.6217 0.02409 0.01464 -0.0194 1.0000 0.0447
-6.000 -0.5831 0.02221 0.01278 -0.0177 0.9926 0.0500
-5.750 -0.5490 0.02126 0.01169 -0.0196 0.9836 0.0545
-5.500 -0.5159 0.02021 0.01069 -0.0216 0.9746 0.0613
-5.250 -0.4838 0.01932 0.00972 -0.0231 0.9649 0.0693
-5.000 -0.4526 0.01845 0.00889 -0.0245 0.9550 0.0847
-4.750 -0.4225 0.01743 0.00805 -0.0258 0.9456 0.1213
-4.500 -0.3997 0.01567 0.00716 -0.0265 0.9348 0.2753
-4.250 -0.3799 0.01462 0.00706 -0.0256 0.9231 0.4755
-4.000 -0.3527 0.01452 0.00708 -0.0252 0.9132 0.5460
-3.750 -0.3252 0.01459 0.00719 -0.0246 0.9042 0.5971
-3.500 -0.3013 0.01485 0.00749 -0.0230 0.8934 0.6405
-3.250 -0.2762 0.01514 0.00779 -0.0215 0.8843 0.6719
-3.000 -0.2499 0.01524 0.00780 -0.0207 0.8752 0.6893
-2.750 -0.2233 0.01521 0.00766 -0.0202 0.8655 0.6977
-2.500 -0.1955 0.01513 0.00743 -0.0201 0.8577 0.7074
-2.250 -0.1692 0.01511 0.00736 -0.0196 0.8480 0.7143
-2.000 -0.1420 0.01503 0.00716 -0.0195 0.8398 0.7231
-1.750 -0.1152 0.01499 0.00706 -0.0191 0.8312 0.7289
-1.500 -0.0883 0.01492 0.00690 -0.0190 0.8230 0.7370
-1.250 -0.0615 0.01488 0.00682 -0.0186 0.8150 0.7430
-1.000 -0.0348 0.01484 0.00672 -0.0184 0.8068 0.7504
-0.750 -0.0080 0.01481 0.00665 -0.0181 0.7994 0.7572
-0.500 0.0185 0.01480 0.00662 -0.0178 0.7916 0.7648
-0.250 0.0452 0.01478 0.00657 -0.0175 0.7843 0.7721
0.000 0.0717 0.01479 0.00657 -0.0172 0.7767 0.7795
0.250 0.0983 0.01479 0.00657 -0.0169 0.7695 0.7873
0.500 0.1248 0.01481 0.00660 -0.0165 0.7628 0.7954
0.750 0.1511 0.01484 0.00666 -0.0162 0.7555 0.8034
1.000 0.1778 0.01486 0.00668 -0.0159 0.7493 0.8120
1.250 0.2040 0.01492 0.00681 -0.0156 0.7416 0.8200
1.500 0.2308 0.01495 0.00685 -0.0153 0.7363 0.8299
1.750 0.2564 0.01504 0.00703 -0.0148 0.7286 0.8380
2.000 0.2828 0.01508 0.00713 -0.0144 0.7225 0.8476
2.250 0.3087 0.01517 0.00731 -0.0140 0.7157 0.8573
2.500 0.3349 0.01523 0.00744 -0.0135 0.7085 0.8668
2.750 0.3608 0.01529 0.00760 -0.0131 0.7008 0.8775
3.000 0.3871 0.01533 0.00774 -0.0126 0.6929 0.8883
3.250 0.4141 0.01540 0.00794 -0.0123 0.6849 0.8989
3.500 0.4419 0.01540 0.00805 -0.0120 0.6762 0.9101
3.750 0.4694 0.01526 0.00797 -0.0114 0.6600 0.9221
4.000 0.4966 0.01499 0.00775 -0.0107 0.6320 0.9345
4.250 0.5258 0.01471 0.00745 -0.0103 0.5904 0.9463
4.500 0.5568 0.01462 0.00730 -0.0106 0.5399 0.9584
4.750 0.5893 0.01475 0.00734 -0.0115 0.4732 0.9710
5.000 0.6131 0.01599 0.00754 -0.0118 0.2752 0.9880
5.250 0.6256 0.01765 0.00844 -0.0108 0.1459 1.0000
5.500 0.6372 0.01873 0.00919 -0.0088 0.0996 1.0000
5.750 0.6530 0.01967 0.00998 -0.0074 0.0790 1.0000
6.000 0.6701 0.02060 0.01083 -0.0062 0.0686 1.0000
6.250 0.6893 0.02139 0.01168 -0.0051 0.0608 1.0000
6.500 0.7068 0.02238 0.01266 -0.0040 0.0555 1.0000
6.750 0.7259 0.02330 0.01366 -0.0030 0.0515 1.0000
7.000 0.7446 0.02428 0.01463 -0.0020 0.0476 1.0000
7.250 0.7633 0.02547 0.01582 -0.0011 0.0446 1.0000
7.500 0.7846 0.02664 0.01709 -0.0003 0.0423 1.0000
7.750 0.8068 0.02795 0.01849 0.0003 0.0404 1.0000
8.000 0.8291 0.02928 0.01988 0.0008 0.0386 1.0000
8.250 0.8508 0.03077 0.02135 0.0011 0.0367 1.0000
8.500 0.8732 0.03255 0.02328 0.0015 0.0349 1.0000
8.750 0.8953 0.03437 0.02539 0.0021 0.0338 1.0000
9.000 0.9157 0.03649 0.02779 0.0028 0.0329 1.0000
9.250 0.9334 0.03880 0.03041 0.0037 0.0321 1.0000
9.500 0.9480 0.04128 0.03322 0.0047 0.0315 1.0000
9.750 0.9590 0.04397 0.03625 0.0060 0.0310 1.0000
10.000 0.9666 0.04663 0.03923 0.0074 0.0305 1.0000
10.250 0.9724 0.04907 0.04191 0.0088 0.0298 1.0000
10.500 0.9766 0.05137 0.04441 0.0101 0.0291 1.0000
10.750 0.9774 0.05362 0.04680 0.0117 0.0284 1.0000
11.000 0.9729 0.05635 0.04969 0.0133 0.0280 1.0000
11.250 0.9643 0.05956 0.05307 0.0147 0.0277 1.0000
11.750 0.9343 0.06719 0.06112 0.0156 0.0275 1.0000
12.000 0.9166 0.07166 0.06580 0.0148 0.0276 1.0000
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Polar data table (+)
Polar graphs
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