NACA 1412 (naca1412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 50,000 Max Cl/Cd: 29.62 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1412-il-50000.txt Download as CSV file: xf-naca1412-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1412
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4999 0.10753 0.09979 0.0051 1.0000 0.3523
-9.000 -0.6909 0.07418 0.06661 -0.0317 1.0000 0.1742
-8.750 -0.6907 0.06927 0.06166 -0.0318 1.0000 0.1732
-8.500 -0.6975 0.06418 0.05644 -0.0317 1.0000 0.1721
-8.250 -0.7049 0.05918 0.05122 -0.0312 1.0000 0.1713
-8.000 -0.7098 0.05444 0.04619 -0.0302 1.0000 0.1708
-7.750 -0.7107 0.05007 0.04144 -0.0288 1.0000 0.1707
-7.500 -0.7078 0.04611 0.03703 -0.0271 1.0000 0.1715
-7.250 -0.7024 0.04262 0.03295 -0.0251 1.0000 0.1738
-7.000 -0.6838 0.04055 0.03098 -0.0238 1.0000 0.1800
-6.750 -0.6704 0.03806 0.02813 -0.0221 1.0000 0.1863
-6.500 -0.6548 0.03551 0.02524 -0.0206 1.0000 0.1923
-6.250 -0.6361 0.03366 0.02326 -0.0191 1.0000 0.2018
-6.000 -0.6172 0.03198 0.02150 -0.0177 1.0000 0.2144
-5.750 -0.5978 0.03032 0.01975 -0.0162 1.0000 0.2293
-5.500 -0.5785 0.02889 0.01825 -0.0147 1.0000 0.2494
-5.250 -0.5588 0.02757 0.01702 -0.0132 1.0000 0.2734
-5.000 -0.5396 0.02640 0.01591 -0.0116 1.0000 0.3034
-4.750 -0.5204 0.02537 0.01507 -0.0098 1.0000 0.3381
-4.500 -0.5014 0.02442 0.01431 -0.0080 1.0000 0.3789
-4.250 -0.4824 0.02354 0.01370 -0.0060 1.0000 0.4236
-4.000 -0.4635 0.02277 0.01317 -0.0038 1.0000 0.4732
-3.750 -0.4449 0.02212 0.01279 -0.0015 1.0000 0.5271
-3.500 -0.4272 0.02162 0.01256 0.0013 1.0000 0.5829
-3.250 -0.4103 0.02127 0.01247 0.0047 1.0000 0.6404
-3.000 -0.3946 0.02104 0.01246 0.0085 1.0000 0.6995
-2.750 -0.3794 0.02097 0.01257 0.0129 1.0000 0.7594
-2.500 -0.3602 0.02114 0.01286 0.0170 1.0000 0.8207
-2.250 -0.3153 0.02173 0.01336 0.0168 1.0000 0.8888
-2.000 -0.1698 0.02270 0.01379 -0.0025 1.0000 0.9559
-1.750 -0.0265 0.02209 0.01272 -0.0252 1.0000 1.0000
-1.500 -0.0445 0.02156 0.01220 -0.0206 1.0000 1.0000
-1.250 -0.0644 0.02118 0.01180 -0.0153 1.0000 1.0000
-1.000 -0.0811 0.02094 0.01153 -0.0102 1.0000 1.0000
-0.750 -0.0901 0.02088 0.01139 -0.0060 1.0000 1.0000
-0.500 -0.0918 0.02098 0.01138 -0.0028 1.0000 1.0000
-0.250 -0.0875 0.02122 0.01151 -0.0005 1.0000 1.0000
0.000 -0.0791 0.02158 0.01176 0.0010 1.0000 1.0000
0.250 -0.0682 0.02203 0.01212 0.0021 1.0000 1.0000
0.500 -0.0558 0.02257 0.01258 0.0029 1.0000 1.0000
0.750 -0.0425 0.02320 0.01314 0.0034 1.0000 1.0000
1.000 0.0185 0.02438 0.01427 -0.0047 0.9836 1.0000
1.250 0.0758 0.02535 0.01522 -0.0119 0.9631 1.0000
1.500 0.1372 0.02626 0.01614 -0.0193 0.9438 1.0000
1.750 0.1837 0.02691 0.01683 -0.0238 0.9216 1.0000
2.000 0.2367 0.02747 0.01745 -0.0291 0.9003 1.0000
2.250 0.2965 0.02782 0.01790 -0.0350 0.8803 1.0000
2.500 0.3372 0.02818 0.01835 -0.0375 0.8573 1.0000
2.750 0.3910 0.02822 0.01852 -0.0415 0.8360 1.0000
3.000 0.4472 0.02791 0.01837 -0.0452 0.8159 1.0000
3.250 0.4775 0.02806 0.01861 -0.0448 0.7916 1.0000
3.500 0.5214 0.02763 0.01831 -0.0457 0.7694 1.0000
3.750 0.5547 0.02742 0.01819 -0.0449 0.7454 1.0000
4.000 0.5881 0.02707 0.01794 -0.0438 0.7208 1.0000
4.250 0.6162 0.02691 0.01784 -0.0419 0.6949 1.0000
4.500 0.6484 0.02644 0.01738 -0.0401 0.6691 1.0000
4.750 0.6714 0.02646 0.01745 -0.0376 0.6395 1.0000
5.000 0.6955 0.02641 0.01739 -0.0351 0.6088 1.0000
5.250 0.7194 0.02636 0.01730 -0.0326 0.5762 1.0000
5.500 0.7426 0.02638 0.01724 -0.0300 0.5417 1.0000
5.750 0.7660 0.02644 0.01713 -0.0274 0.5055 1.0000
6.000 0.7841 0.02688 0.01751 -0.0247 0.4655 1.0000
6.250 0.8050 0.02718 0.01753 -0.0221 0.4246 1.0000
6.500 0.8212 0.02783 0.01806 -0.0193 0.3812 1.0000
6.750 0.8381 0.02860 0.01856 -0.0167 0.3392 1.0000
7.000 0.8547 0.02959 0.01930 -0.0143 0.3001 1.0000
7.250 0.8727 0.03088 0.02031 -0.0124 0.2665 1.0000
7.500 0.8903 0.03247 0.02187 -0.0106 0.2386 1.0000
7.750 0.9114 0.03420 0.02338 -0.0093 0.2171 1.0000
8.000 0.9315 0.03624 0.02548 -0.0081 0.2012 1.0000
8.250 0.9527 0.03827 0.02751 -0.0070 0.1882 1.0000
8.500 0.9668 0.04062 0.03028 -0.0052 0.1783 1.0000
8.750 0.9870 0.04319 0.03289 -0.0043 0.1712 1.0000
9.000 0.9950 0.04637 0.03663 -0.0022 0.1667 1.0000
9.250 1.0073 0.04921 0.03971 -0.0007 0.1617 1.0000
9.500 1.0233 0.05216 0.04268 0.0002 0.1568 1.0000
9.750 1.0172 0.05608 0.04717 0.0029 0.1549 1.0000
10.000 1.0079 0.06045 0.05196 0.0051 0.1540 1.0000
10.250 0.9926 0.06524 0.05710 0.0071 0.1542 1.0000
10.500 0.9703 0.07043 0.06255 0.0087 0.1550 1.0000
10.750 0.9445 0.07571 0.06799 0.0100 0.1561 1.0000
11.000 0.9229 0.08150 0.07387 0.0099 0.1572 1.0000
11.250 0.7325 0.11804 0.11023 -0.0187 0.1995 1.0000
11.500 0.7469 0.12275 0.11499 -0.0186 0.2026 1.0000
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Polar data table (+)
Polar graphs
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