NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 500,000 Max Cl/Cd: 45.56 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001234-il-500000-n5.txt Download as CSV file: xf-naca001234-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8029 0.06148 0.05877 -0.0435 1.0000 0.0034
-12.000 -0.8242 0.05564 0.05274 -0.0456 1.0000 0.0034
-11.750 -0.8456 0.05056 0.04744 -0.0458 1.0000 0.0034
-11.500 -0.8652 0.04623 0.04287 -0.0446 1.0000 0.0034
-11.250 -0.8836 0.04241 0.03879 -0.0420 1.0000 0.0034
-11.000 -0.9016 0.03892 0.03502 -0.0383 1.0000 0.0035
-10.750 -0.9116 0.03656 0.03245 -0.0344 1.0000 0.0036
-10.500 -0.9177 0.03488 0.03061 -0.0301 1.0000 0.0036
-10.250 -0.9204 0.03391 0.02954 -0.0257 1.0000 0.0037
-10.000 -0.9197 0.03276 0.02826 -0.0219 1.0000 0.0038
-9.750 -0.9173 0.03176 0.02713 -0.0181 1.0000 0.0039
-9.500 -0.9145 0.03069 0.02592 -0.0143 1.0000 0.0040
-9.250 -0.9120 0.02935 0.02441 -0.0103 1.0000 0.0042
-9.000 -0.8976 0.02743 0.02224 -0.0088 0.9987 0.0044
-8.750 -0.8766 0.02509 0.01959 -0.0084 0.9967 0.0045
-8.500 -0.8533 0.02313 0.01735 -0.0083 0.9951 0.0047
-8.250 -0.8298 0.02152 0.01553 -0.0082 0.9929 0.0050
-8.000 -0.8053 0.02019 0.01401 -0.0081 0.9906 0.0052
-7.750 -0.7790 0.01911 0.01278 -0.0084 0.9885 0.0054
-7.500 -0.7546 0.01769 0.01123 -0.0086 0.9867 0.0057
-7.250 -0.7296 0.01687 0.01032 -0.0087 0.9838 0.0061
-7.000 -0.7023 0.01630 0.00971 -0.0092 0.9810 0.0067
-6.750 -0.6736 0.01570 0.00905 -0.0099 0.9789 0.0074
-6.500 -0.6450 0.01502 0.00828 -0.0106 0.9770 0.0080
-6.250 -0.6201 0.01437 0.00755 -0.0104 0.9732 0.0085
-6.000 -0.5965 0.01352 0.00660 -0.0100 0.9691 0.0097
-5.750 -0.5681 0.01304 0.00608 -0.0105 0.9664 0.0111
-5.500 -0.5406 0.01266 0.00563 -0.0109 0.9631 0.0129
-5.250 -0.5159 0.01226 0.00515 -0.0104 0.9579 0.0148
-5.000 -0.4889 0.01182 0.00468 -0.0105 0.9541 0.0211
-4.750 -0.4618 0.01144 0.00432 -0.0106 0.9504 0.0331
-4.250 -0.4171 0.01023 0.00354 -0.0092 0.9393 0.1385
-4.000 -0.3981 0.00942 0.00316 -0.0080 0.9331 0.2434
-3.750 -0.3796 0.00859 0.00282 -0.0066 0.9267 0.3614
-3.500 -0.3602 0.00794 0.00256 -0.0053 0.9206 0.4588
-3.250 -0.3399 0.00746 0.00236 -0.0039 0.9137 0.5349
-3.000 -0.3172 0.00711 0.00220 -0.0030 0.9079 0.5924
-2.750 -0.2942 0.00687 0.00210 -0.0020 0.9008 0.6384
-2.500 -0.2683 0.00671 0.00198 -0.0017 0.8950 0.6670
-2.250 -0.2425 0.00661 0.00190 -0.0013 0.8874 0.6865
-2.000 -0.2157 0.00651 0.00181 -0.0011 0.8809 0.7056
-1.750 -0.1896 0.00643 0.00174 -0.0008 0.8726 0.7249
-1.500 -0.1629 0.00636 0.00168 -0.0006 0.8646 0.7419
-1.250 -0.1360 0.00631 0.00163 -0.0004 0.8560 0.7563
-1.000 -0.1090 0.00627 0.00159 -0.0003 0.8473 0.7692
-0.750 -0.0818 0.00624 0.00156 -0.0002 0.8391 0.7808
-0.500 -0.0546 0.00622 0.00154 -0.0001 0.8300 0.7916
-0.250 -0.0273 0.00621 0.00152 -0.0001 0.8211 0.8019
0.000 0.0000 0.00621 0.00151 0.0000 0.8120 0.8120
0.250 0.0273 0.00621 0.00152 0.0001 0.8019 0.8211
0.500 0.0546 0.00622 0.00154 0.0001 0.7916 0.8300
0.750 0.0818 0.00624 0.00156 0.0002 0.7809 0.8391
1.000 0.1091 0.00627 0.00159 0.0003 0.7693 0.8473
1.250 0.1360 0.00631 0.00163 0.0004 0.7563 0.8560
1.500 0.1629 0.00636 0.00168 0.0006 0.7419 0.8646
1.750 0.1896 0.00643 0.00174 0.0008 0.7249 0.8726
2.000 0.2157 0.00651 0.00181 0.0011 0.7055 0.8808
2.250 0.2425 0.00661 0.00190 0.0013 0.6865 0.8874
2.500 0.2683 0.00671 0.00198 0.0017 0.6672 0.8950
2.750 0.2942 0.00687 0.00210 0.0020 0.6382 0.9007
3.000 0.3172 0.00712 0.00220 0.0030 0.5922 0.9079
3.250 0.3399 0.00746 0.00236 0.0039 0.5347 0.9137
3.500 0.3603 0.00794 0.00256 0.0052 0.4590 0.9205
3.750 0.3797 0.00859 0.00282 0.0066 0.3616 0.9267
4.000 0.3981 0.00942 0.00316 0.0080 0.2425 0.9330
4.250 0.4171 0.01023 0.00354 0.0092 0.1379 0.9393
4.750 0.4619 0.01143 0.00432 0.0106 0.0330 0.9504
5.000 0.4889 0.01182 0.00468 0.0105 0.0211 0.9540
5.250 0.5160 0.01225 0.00514 0.0104 0.0149 0.9578
5.500 0.5408 0.01266 0.00563 0.0108 0.0129 0.9630
5.750 0.5682 0.01304 0.00607 0.0105 0.0111 0.9663
6.000 0.5966 0.01352 0.00660 0.0100 0.0097 0.9691
6.250 0.6201 0.01439 0.00757 0.0104 0.0085 0.9733
6.500 0.6451 0.01502 0.00828 0.0106 0.0080 0.9770
6.750 0.6738 0.01570 0.00905 0.0099 0.0074 0.9789
7.000 0.7026 0.01628 0.00969 0.0091 0.0066 0.9810
7.250 0.7297 0.01687 0.01032 0.0086 0.0061 0.9839
7.500 0.7549 0.01769 0.01123 0.0085 0.0057 0.9867
7.750 0.7792 0.01912 0.01279 0.0084 0.0054 0.9886
8.000 0.8055 0.02020 0.01402 0.0081 0.0052 0.9906
8.250 0.8301 0.02152 0.01553 0.0081 0.0050 0.9930
8.500 0.8536 0.02313 0.01735 0.0083 0.0047 0.9951
8.750 0.8770 0.02510 0.01959 0.0083 0.0045 0.9967
9.000 0.8979 0.02745 0.02226 0.0087 0.0044 0.9987
9.250 0.9117 0.02939 0.02446 0.0104 0.0042 1.0000
9.500 0.9147 0.03063 0.02586 0.0143 0.0040 1.0000
9.750 0.9175 0.03172 0.02709 0.0181 0.0039 1.0000
10.000 0.9190 0.03289 0.02841 0.0220 0.0038 1.0000
10.250 0.9201 0.03399 0.02963 0.0258 0.0037 1.0000
10.500 0.9179 0.03492 0.03065 0.0301 0.0036 1.0000
10.750 0.9123 0.03655 0.03244 0.0343 0.0036 1.0000
11.000 0.9017 0.03899 0.03510 0.0382 0.0035 1.0000
11.250 0.8849 0.04238 0.03876 0.0419 0.0034 1.0000
11.500 0.8658 0.04627 0.04291 0.0445 0.0034 1.0000
11.750 0.8459 0.05065 0.04753 0.0457 0.0034 1.0000
12.000 0.8246 0.05573 0.05283 0.0454 0.0034 1.0000
12.500 0.7833 0.06857 0.06605 0.0393 0.0035 1.0000
12.750 0.7451 0.08192 0.07965 0.0305 0.0036 1.0000
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Polar data table (+)
Polar graphs
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