NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 200,000 Max Cl/Cd: 67.93 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651412-il-200000-n5.txt Download as CSV file: xf-naca651412-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4585 0.08571 0.08206 -0.0540 1.0000 0.0188
-10.250 -0.4696 0.07899 0.07539 -0.0577 1.0000 0.0187
-10.000 -0.4825 0.07211 0.06855 -0.0623 1.0000 0.0185
-9.750 -0.5025 0.06639 0.06282 -0.0654 1.0000 0.0183
-9.500 -0.5274 0.06272 0.05916 -0.0652 1.0000 0.0181
-9.250 -0.5447 0.05815 0.05448 -0.0676 0.9908 0.0180
-9.000 -0.5469 0.05107 0.04705 -0.0731 0.9779 0.0180
-8.750 -0.5434 0.04465 0.04018 -0.0763 0.9677 0.0182
-8.500 -0.5353 0.03884 0.03379 -0.0780 0.9585 0.0185
-8.250 -0.5201 0.03400 0.02829 -0.0792 0.9509 0.0190
-8.000 -0.5011 0.03158 0.02559 -0.0797 0.9428 0.0200
-7.750 -0.4752 0.03014 0.02400 -0.0809 0.9371 0.0208
-7.500 -0.4517 0.02836 0.02196 -0.0813 0.9301 0.0217
-7.250 -0.4278 0.02618 0.01941 -0.0814 0.9233 0.0224
-7.000 -0.4024 0.02431 0.01718 -0.0816 0.9171 0.0232
-6.750 -0.3776 0.02286 0.01543 -0.0813 0.9098 0.0241
-6.500 -0.3496 0.02180 0.01406 -0.0816 0.9047 0.0255
-6.250 -0.3265 0.02031 0.01249 -0.0812 0.8968 0.0264
-6.000 -0.2999 0.01928 0.01135 -0.0812 0.8911 0.0273
-5.750 -0.2753 0.01844 0.01043 -0.0809 0.8841 0.0282
-5.500 -0.2497 0.01767 0.00958 -0.0806 0.8778 0.0294
-5.250 -0.2243 0.01705 0.00888 -0.0803 0.8715 0.0313
-5.000 -0.1994 0.01647 0.00820 -0.0799 0.8646 0.0327
-4.750 -0.1742 0.01578 0.00743 -0.0796 0.8591 0.0337
-4.500 -0.1514 0.01501 0.00665 -0.0791 0.8519 0.0355
-4.250 -0.1259 0.01449 0.00607 -0.0789 0.8464 0.0377
-4.000 -0.1004 0.01412 0.00564 -0.0787 0.8400 0.0410
-3.750 -0.0744 0.01376 0.00519 -0.0786 0.8338 0.0444
-3.500 -0.0480 0.01333 0.00471 -0.0785 0.8287 0.0499
-3.250 -0.0221 0.01299 0.00436 -0.0784 0.8223 0.0599
-3.000 0.0034 0.01236 0.00399 -0.0785 0.8171 0.1225
-2.750 0.0248 0.01080 0.00356 -0.0788 0.8114 0.4087
-2.500 0.0479 0.01031 0.00372 -0.0780 0.8054 0.5941
-2.250 0.0734 0.01033 0.00388 -0.0771 0.8007 0.6628
-2.000 0.0984 0.01046 0.00408 -0.0761 0.7952 0.7023
-1.750 0.1243 0.01056 0.00417 -0.0755 0.7899 0.7220
-1.500 0.1523 0.01058 0.00410 -0.0754 0.7855 0.7322
-1.250 0.1796 0.01058 0.00406 -0.0754 0.7800 0.7372
-1.000 0.2077 0.01058 0.00399 -0.0755 0.7748 0.7431
-0.750 0.2360 0.01058 0.00393 -0.0756 0.7707 0.7480
-0.500 0.2634 0.01060 0.00393 -0.0756 0.7655 0.7531
-0.250 0.2914 0.01062 0.00391 -0.0758 0.7603 0.7591
0.000 0.3193 0.01063 0.00390 -0.0758 0.7561 0.7639
0.250 0.3468 0.01067 0.00394 -0.0758 0.7513 0.7692
0.500 0.3747 0.01071 0.00396 -0.0759 0.7462 0.7754
0.750 0.4022 0.01073 0.00400 -0.0759 0.7419 0.7802
1.000 0.4298 0.01078 0.00406 -0.0759 0.7375 0.7860
1.250 0.4573 0.01084 0.00415 -0.0760 0.7323 0.7921
1.500 0.4844 0.01088 0.00423 -0.0758 0.7279 0.7972
1.750 0.5124 0.01094 0.00431 -0.0759 0.7239 0.8036
2.000 0.5388 0.01102 0.00446 -0.0757 0.7185 0.8095
2.250 0.5658 0.01108 0.00458 -0.0756 0.7139 0.8155
2.500 0.5942 0.01115 0.00468 -0.0757 0.7100 0.8223
2.750 0.6194 0.01123 0.00488 -0.0753 0.7041 0.8283
3.000 0.6465 0.01129 0.00500 -0.0752 0.6980 0.8358
3.250 0.6717 0.01133 0.00513 -0.0746 0.6895 0.8420
3.500 0.6972 0.01132 0.00515 -0.0739 0.6766 0.8494
3.750 0.7202 0.01127 0.00514 -0.0727 0.6568 0.8566
4.000 0.7422 0.01123 0.00506 -0.0712 0.6247 0.8653
4.250 0.7614 0.01129 0.00501 -0.0691 0.5798 0.8734
4.500 0.7812 0.01150 0.00508 -0.0674 0.5284 0.8828
4.750 0.7918 0.01213 0.00526 -0.0641 0.4269 0.8936
5.000 0.7928 0.01347 0.00589 -0.0596 0.2915 0.9078
5.250 0.7968 0.01474 0.00663 -0.0560 0.1814 0.9243
5.500 0.8033 0.01594 0.00735 -0.0528 0.0909 0.9447
5.750 0.8221 0.01682 0.00803 -0.0519 0.0538 0.9737
6.000 0.8432 0.01751 0.00868 -0.0514 0.0432 1.0000
6.250 0.8634 0.01818 0.00936 -0.0506 0.0375 1.0000
6.500 0.8813 0.01896 0.01018 -0.0494 0.0337 1.0000
6.750 0.8988 0.01964 0.01095 -0.0481 0.0315 1.0000
7.000 0.9152 0.02041 0.01177 -0.0467 0.0295 1.0000
7.250 0.9303 0.02127 0.01265 -0.0452 0.0276 1.0000
7.500 0.9415 0.02246 0.01385 -0.0432 0.0259 1.0000
7.750 0.9582 0.02328 0.01477 -0.0419 0.0248 1.0000
8.000 0.9736 0.02428 0.01585 -0.0406 0.0239 1.0000
8.250 0.9896 0.02533 0.01697 -0.0393 0.0230 1.0000
8.500 1.0062 0.02643 0.01813 -0.0382 0.0222 1.0000
8.750 1.0237 0.02757 0.01934 -0.0371 0.0215 1.0000
9.000 1.0420 0.02877 0.02059 -0.0363 0.0210 1.0000
9.250 1.0613 0.03007 0.02194 -0.0356 0.0204 1.0000
9.500 1.0831 0.03164 0.02355 -0.0352 0.0199 1.0000
9.750 1.1076 0.03352 0.02556 -0.0352 0.0193 1.0000
10.000 1.1254 0.03486 0.02713 -0.0343 0.0188 1.0000
10.250 1.1427 0.03644 0.02893 -0.0334 0.0181 1.0000
10.500 1.1593 0.03835 0.03109 -0.0325 0.0177 1.0000
10.750 1.1729 0.04046 0.03345 -0.0313 0.0173 1.0000
11.000 1.1830 0.04274 0.03600 -0.0299 0.0171 1.0000
11.250 1.1891 0.04515 0.03867 -0.0282 0.0168 1.0000
11.500 1.1915 0.04773 0.04152 -0.0263 0.0165 1.0000
11.750 1.1907 0.05050 0.04455 -0.0245 0.0164 1.0000
12.000 1.1871 0.05340 0.04771 -0.0228 0.0162 1.0000
12.250 1.1818 0.05639 0.05094 -0.0213 0.0160 1.0000
12.500 1.1767 0.05931 0.05404 -0.0202 0.0158 1.0000
12.750 1.1694 0.06250 0.05742 -0.0194 0.0155 1.0000
13.000 1.1608 0.06593 0.06102 -0.0191 0.0154 1.0000
13.250 1.1487 0.07004 0.06534 -0.0191 0.0152 1.0000
13.500 1.1370 0.07424 0.06971 -0.0196 0.0151 1.0000
13.750 1.1207 0.07940 0.07506 -0.0208 0.0150 1.0000
14.000 1.1018 0.08529 0.08116 -0.0228 0.0150 1.0000
14.250 1.0800 0.09217 0.08826 -0.0258 0.0150 1.0000
14.500 1.0433 0.10297 0.09937 -0.0317 0.0152 1.0000
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