NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 200,000 Max Cl/Cd: 39.66 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001234-il-200000-n5.txt Download as CSV file: xf-naca001234-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6731 0.08328 0.07970 -0.0367 1.0000 0.0092
-11.500 -0.7005 0.07365 0.06988 -0.0429 1.0000 0.0089
-11.250 -0.7217 0.06737 0.06342 -0.0458 1.0000 0.0087
-11.000 -0.7401 0.06260 0.05846 -0.0467 1.0000 0.0087
-10.750 -0.7567 0.05871 0.05438 -0.0462 1.0000 0.0086
-10.500 -0.7724 0.05536 0.05084 -0.0443 1.0000 0.0086
-10.250 -0.7876 0.05241 0.04770 -0.0413 1.0000 0.0086
-10.000 -0.8022 0.04988 0.04497 -0.0372 1.0000 0.0085
-9.750 -0.8160 0.04752 0.04240 -0.0323 1.0000 0.0085
-9.500 -0.8260 0.04492 0.03957 -0.0277 1.0000 0.0085
-9.250 -0.8336 0.04233 0.03672 -0.0231 1.0000 0.0086
-9.000 -0.8384 0.03975 0.03386 -0.0186 1.0000 0.0086
-8.750 -0.8401 0.03726 0.03109 -0.0143 1.0000 0.0087
-8.500 -0.8383 0.03498 0.02854 -0.0104 1.0000 0.0089
-8.250 -0.8333 0.03298 0.02631 -0.0070 1.0000 0.0091
-8.000 -0.8255 0.03124 0.02435 -0.0038 1.0000 0.0093
-7.750 -0.8159 0.03004 0.02299 -0.0010 1.0000 0.0098
-7.500 -0.8046 0.02901 0.02182 0.0016 1.0000 0.0105
-7.250 -0.7918 0.02787 0.02050 0.0041 1.0000 0.0112
-7.000 -0.7772 0.02641 0.01878 0.0064 1.0000 0.0118
-6.750 -0.7501 0.02459 0.01673 0.0063 0.9982 0.0123
-6.500 -0.7218 0.02303 0.01498 0.0059 0.9961 0.0129
-6.250 -0.6937 0.02177 0.01356 0.0054 0.9937 0.0136
-6.000 -0.6708 0.01997 0.01167 0.0058 0.9905 0.0156
-5.750 -0.6441 0.01890 0.01051 0.0053 0.9874 0.0177
-5.500 -0.6174 0.01801 0.00951 0.0051 0.9839 0.0198
-5.250 -0.5898 0.01733 0.00866 0.0047 0.9800 0.0234
-5.000 -0.5604 0.01657 0.00782 0.0039 0.9771 0.0291
-4.750 -0.5342 0.01589 0.00712 0.0037 0.9728 0.0424
-4.500 -0.5100 0.01482 0.00641 0.0037 0.9684 0.1134
-4.250 -0.4894 0.01316 0.00573 0.0037 0.9650 0.3116
-4.000 -0.4740 0.01212 0.00535 0.0055 0.9583 0.4553
-3.750 -0.4509 0.01137 0.00516 0.0062 0.9543 0.5768
-3.500 -0.4220 0.01099 0.00513 0.0061 0.9518 0.6685
-3.250 -0.3984 0.01086 0.00509 0.0071 0.9456 0.7113
-3.000 -0.3669 0.01079 0.00498 0.0064 0.9419 0.7345
-2.750 -0.3336 0.01071 0.00485 0.0052 0.9390 0.7538
-2.500 -0.3049 0.01068 0.00478 0.0051 0.9339 0.7712
-2.250 -0.2750 0.01064 0.00470 0.0047 0.9289 0.7868
-2.000 -0.2419 0.01060 0.00461 0.0036 0.9254 0.8005
-1.750 -0.2134 0.01057 0.00456 0.0035 0.9197 0.8131
-1.500 -0.1828 0.01056 0.00450 0.0030 0.9143 0.8238
-1.250 -0.1489 0.01052 0.00444 0.0017 0.9106 0.8333
-1.000 -0.1221 0.01052 0.00441 0.0020 0.9030 0.8433
-0.750 -0.0905 0.01048 0.00434 0.0012 0.8976 0.8526
-0.500 -0.0605 0.01049 0.00435 0.0009 0.8904 0.8602
-0.250 -0.0305 0.01044 0.00429 0.0005 0.8837 0.8690
0.000 0.0000 0.01047 0.00432 0.0000 0.8759 0.8759
0.250 0.0305 0.01044 0.00429 -0.0005 0.8690 0.8837
0.500 0.0605 0.01049 0.00435 -0.0009 0.8602 0.8904
0.750 0.0905 0.01048 0.00434 -0.0012 0.8526 0.8976
1.000 0.1221 0.01052 0.00441 -0.0020 0.8433 0.9030
1.250 0.1489 0.01052 0.00444 -0.0017 0.8333 0.9106
1.500 0.1828 0.01056 0.00450 -0.0030 0.8238 0.9143
1.750 0.2134 0.01057 0.00456 -0.0035 0.8130 0.9198
2.000 0.2419 0.01060 0.00461 -0.0036 0.8005 0.9254
2.250 0.2750 0.01064 0.00470 -0.0047 0.7868 0.9289
2.500 0.3048 0.01067 0.00478 -0.0051 0.7712 0.9339
2.750 0.3335 0.01071 0.00485 -0.0052 0.7538 0.9390
3.000 0.3669 0.01078 0.00498 -0.0064 0.7345 0.9419
3.250 0.3983 0.01086 0.00509 -0.0071 0.7113 0.9456
3.500 0.4220 0.01098 0.00512 -0.0061 0.6685 0.9518
3.750 0.4509 0.01137 0.00515 -0.0062 0.5767 0.9543
4.000 0.4740 0.01212 0.00535 -0.0055 0.4556 0.9583
4.250 0.4894 0.01316 0.00573 -0.0037 0.3113 0.9650
4.500 0.5100 0.01482 0.00641 -0.0037 0.1134 0.9684
4.750 0.5342 0.01588 0.00711 -0.0037 0.0424 0.9728
5.000 0.5605 0.01656 0.00782 -0.0039 0.0291 0.9771
5.250 0.5898 0.01733 0.00866 -0.0047 0.0234 0.9801
5.500 0.6174 0.01800 0.00950 -0.0051 0.0198 0.9839
5.750 0.6441 0.01889 0.01051 -0.0054 0.0177 0.9875
6.000 0.6709 0.01997 0.01167 -0.0058 0.0156 0.9905
6.250 0.6938 0.02177 0.01356 -0.0055 0.0136 0.9938
6.500 0.7219 0.02303 0.01498 -0.0059 0.0129 0.9961
6.750 0.7503 0.02459 0.01672 -0.0063 0.0123 0.9982
7.000 0.7770 0.02640 0.01877 -0.0064 0.0118 1.0000
7.250 0.7917 0.02785 0.02049 -0.0041 0.0112 1.0000
7.500 0.8045 0.02900 0.02181 -0.0016 0.0105 1.0000
7.750 0.8157 0.03006 0.02301 0.0010 0.0098 1.0000
8.000 0.8254 0.03124 0.02434 0.0038 0.0093 1.0000
8.250 0.8332 0.03297 0.02629 0.0070 0.0091 1.0000
8.500 0.8382 0.03497 0.02853 0.0105 0.0089 1.0000
8.750 0.8401 0.03725 0.03108 0.0143 0.0087 1.0000
9.000 0.8385 0.03973 0.03383 0.0186 0.0086 1.0000
9.250 0.8337 0.04233 0.03671 0.0231 0.0086 1.0000
9.500 0.8262 0.04493 0.03957 0.0277 0.0085 1.0000
9.750 0.8163 0.04752 0.04240 0.0322 0.0085 1.0000
10.000 0.8026 0.04989 0.04498 0.0371 0.0085 1.0000
10.250 0.7881 0.05243 0.04771 0.0412 0.0086 1.0000
10.500 0.7729 0.05539 0.05087 0.0442 0.0086 1.0000
10.750 0.7575 0.05872 0.05440 0.0460 0.0086 1.0000
11.000 0.7405 0.06267 0.05853 0.0466 0.0087 1.0000
11.250 0.7223 0.06744 0.06349 0.0456 0.0088 1.0000
11.500 0.7012 0.07373 0.06997 0.0427 0.0089 1.0000
11.750 0.6737 0.08346 0.07988 0.0364 0.0092 1.0000
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Polar data table (+)
Polar graphs
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