NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 50,000 Max Cl/Cd: 25.93 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001234-il-50000.txt Download as CSV file: xf-naca001234-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6304 0.09725 0.09044 -0.0247 1.0000 0.1825
-9.750 -0.6668 0.08674 0.08006 -0.0332 1.0000 0.1577
-9.500 -0.7097 0.08125 0.07459 -0.0345 1.0000 0.1546
-9.250 -0.7325 0.07621 0.06949 -0.0333 1.0000 0.1441
-9.000 -0.7750 0.07221 0.06525 -0.0300 1.0000 0.1397
-8.750 -0.7807 0.06716 0.05999 -0.0280 1.0000 0.1288
-8.500 -0.7946 0.06312 0.05557 -0.0243 1.0000 0.1209
-8.250 -0.8039 0.05893 0.05100 -0.0205 1.0000 0.1145
-8.000 -0.8079 0.05554 0.04707 -0.0164 1.0000 0.1086
-7.750 -0.8022 0.05173 0.04297 -0.0134 1.0000 0.1051
-7.500 -0.7984 0.04826 0.03897 -0.0097 1.0000 0.1013
-7.250 -0.7942 0.04577 0.03564 -0.0052 1.0000 0.0979
-7.000 -0.7797 0.04309 0.03251 -0.0025 1.0000 0.0974
-6.750 -0.7589 0.03961 0.02896 -0.0016 1.0000 0.1012
-6.500 -0.7381 0.03715 0.02622 0.0001 1.0000 0.1048
-6.250 -0.7114 0.03470 0.02339 0.0012 1.0000 0.1074
-6.000 -0.6766 0.03223 0.02070 0.0012 1.0000 0.1124
-5.750 -0.6427 0.03011 0.01866 0.0008 1.0000 0.1271
-5.500 -0.6139 0.02820 0.01686 0.0015 1.0000 0.1452
-5.250 -0.5997 0.02636 0.01522 0.0042 1.0000 0.1780
-5.000 -0.6032 0.02327 0.01359 0.0092 1.0000 0.2994
-4.750 -0.4085 0.03433 0.02537 0.0087 1.0000 0.8524
-4.500 -0.3529 0.03390 0.02445 0.0035 1.0000 0.8795
-4.250 -0.3002 0.03321 0.02334 -0.0018 1.0000 0.9051
-4.000 -0.2508 0.03233 0.02209 -0.0071 1.0000 0.9298
-3.750 -0.1962 0.03124 0.02068 -0.0137 1.0000 0.9529
-3.500 -0.1381 0.02989 0.01902 -0.0215 1.0000 0.9744
-3.250 -0.0769 0.02839 0.01726 -0.0303 1.0000 0.9951
-3.000 -0.0523 0.02745 0.01621 -0.0321 1.0000 1.0000
-2.750 -0.0437 0.02685 0.01556 -0.0306 1.0000 1.0000
-2.500 -0.0359 0.02633 0.01498 -0.0288 1.0000 1.0000
-2.250 -0.0288 0.02588 0.01449 -0.0268 1.0000 1.0000
-2.000 -0.0224 0.02550 0.01408 -0.0246 1.0000 1.0000
-1.750 -0.0170 0.02517 0.01374 -0.0222 1.0000 1.0000
-1.500 -0.0125 0.02491 0.01346 -0.0195 1.0000 1.0000
-1.250 -0.0089 0.02470 0.01324 -0.0166 1.0000 1.0000
-1.000 -0.0061 0.02453 0.01307 -0.0135 1.0000 1.0000
-0.750 -0.0040 0.02441 0.01293 -0.0102 1.0000 1.0000
-0.500 -0.0024 0.02432 0.01284 -0.0069 1.0000 1.0000
-0.250 -0.0011 0.02427 0.01279 -0.0035 1.0000 1.0000
0.000 0.0000 0.02426 0.01277 0.0000 1.0000 1.0000
0.250 0.0011 0.02427 0.01278 0.0035 1.0000 1.0000
0.500 0.0024 0.02432 0.01284 0.0069 1.0000 1.0000
0.750 0.0040 0.02441 0.01292 0.0102 1.0000 1.0000
1.000 0.0061 0.02453 0.01306 0.0135 1.0000 1.0000
1.250 0.0089 0.02469 0.01323 0.0166 1.0000 1.0000
1.500 0.0125 0.02490 0.01345 0.0195 1.0000 1.0000
1.750 0.0170 0.02516 0.01373 0.0222 1.0000 1.0000
2.000 0.0225 0.02549 0.01407 0.0246 1.0000 1.0000
2.250 0.0289 0.02587 0.01448 0.0268 1.0000 1.0000
2.500 0.0359 0.02632 0.01496 0.0288 1.0000 1.0000
2.750 0.0438 0.02683 0.01554 0.0306 1.0000 1.0000
3.000 0.0524 0.02743 0.01619 0.0321 1.0000 1.0000
3.250 0.0768 0.02837 0.01724 0.0303 0.9952 1.0000
3.500 0.1380 0.02987 0.01900 0.0215 0.9745 1.0000
3.750 0.1963 0.03122 0.02066 0.0137 0.9530 1.0000
4.000 0.2507 0.03231 0.02207 0.0071 0.9299 1.0000
4.250 0.3003 0.03319 0.02332 0.0018 0.9052 1.0000
4.500 0.3530 0.03389 0.02443 -0.0035 0.8795 1.0000
4.750 0.4087 0.03431 0.02535 -0.0087 0.8524 1.0000
5.000 0.6032 0.02326 0.01358 -0.0092 0.3001 1.0000
5.250 0.5996 0.02635 0.01521 -0.0042 0.1783 1.0000
5.500 0.6139 0.02819 0.01686 -0.0015 0.1453 1.0000
5.750 0.6426 0.03010 0.01865 -0.0008 0.1272 1.0000
6.000 0.6765 0.03223 0.02069 -0.0011 0.1124 1.0000
6.250 0.7113 0.03469 0.02338 -0.0012 0.1074 1.0000
6.500 0.7381 0.03715 0.02621 -0.0001 0.1048 1.0000
6.750 0.7588 0.03960 0.02895 0.0016 0.1012 1.0000
7.000 0.7797 0.04308 0.03249 0.0025 0.0975 1.0000
7.250 0.7942 0.04576 0.03563 0.0052 0.0979 1.0000
7.500 0.7984 0.04826 0.03896 0.0097 0.1013 1.0000
7.750 0.8022 0.05173 0.04296 0.0134 0.1051 1.0000
8.000 0.8079 0.05554 0.04706 0.0164 0.1086 1.0000
8.250 0.8039 0.05893 0.05100 0.0205 0.1145 1.0000
8.500 0.7947 0.06312 0.05558 0.0243 0.1209 1.0000
8.750 0.7807 0.06716 0.06000 0.0279 0.1288 1.0000
9.000 0.7749 0.07222 0.06526 0.0300 0.1397 1.0000
9.250 0.7325 0.07624 0.06951 0.0332 0.1442 1.0000
9.500 0.7095 0.08129 0.07463 0.0344 0.1546 1.0000
9.750 0.6668 0.08683 0.08015 0.0331 0.1579 1.0000
10.000 0.6296 0.09745 0.09063 0.0243 0.1828 1.0000
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Polar data table (+)
Polar graphs
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