NACA 2410 (naca2410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 50,000 Max Cl/Cd: 35.35 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2410-il-50000.txt Download as CSV file: xf-naca2410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4636 0.09537 0.08827 -0.0037 1.0000 0.3393
-7.750 -0.4650 0.09272 0.08568 -0.0030 1.0000 0.3555
-7.500 -0.4685 0.09019 0.08323 -0.0020 1.0000 0.3717
-7.250 -0.4655 0.08709 0.08017 -0.0007 1.0000 0.3876
-7.000 -0.4620 0.08399 0.07713 0.0007 1.0000 0.4033
-6.500 -0.5338 0.05453 0.04680 -0.0382 1.0000 0.1719
-6.250 -0.5216 0.05040 0.04250 -0.0377 1.0000 0.1701
-6.000 -0.5089 0.04627 0.03810 -0.0374 1.0000 0.1674
-5.750 -0.4951 0.04231 0.03371 -0.0371 1.0000 0.1665
-5.500 -0.4794 0.03893 0.02974 -0.0367 1.0000 0.1699
-5.250 -0.4609 0.03598 0.02637 -0.0360 1.0000 0.1732
-5.000 -0.4403 0.03363 0.02382 -0.0351 1.0000 0.1768
-4.750 -0.4184 0.03141 0.02120 -0.0343 1.0000 0.1822
-4.500 -0.3965 0.02965 0.01923 -0.0335 1.0000 0.1924
-4.250 -0.3733 0.02798 0.01728 -0.0328 1.0000 0.2046
-4.000 -0.3492 0.02641 0.01553 -0.0320 1.0000 0.2187
-3.750 -0.3260 0.02513 0.01433 -0.0311 1.0000 0.2413
-3.500 -0.3023 0.02391 0.01313 -0.0303 1.0000 0.2753
-3.250 -0.2789 0.02274 0.01213 -0.0294 1.0000 0.3254
-3.000 -0.2564 0.02157 0.01139 -0.0282 1.0000 0.3941
-2.750 -0.2344 0.02038 0.01077 -0.0267 1.0000 0.4922
-2.500 -0.2174 0.01919 0.01047 -0.0234 1.0000 0.6319
-2.250 -0.1409 0.01829 0.01029 -0.0271 1.0000 1.0000
-2.000 -0.1345 0.01810 0.00968 -0.0254 1.0000 1.0000
-1.750 -0.1191 0.01815 0.00939 -0.0244 1.0000 1.0000
-1.500 -0.1017 0.01830 0.00924 -0.0236 1.0000 1.0000
-1.250 -0.0834 0.01850 0.00920 -0.0229 1.0000 1.0000
-1.000 -0.0647 0.01877 0.00924 -0.0223 1.0000 1.0000
-0.750 -0.0459 0.01909 0.00937 -0.0218 1.0000 1.0000
-0.500 -0.0269 0.01947 0.00959 -0.0214 1.0000 1.0000
-0.250 -0.0081 0.01991 0.00988 -0.0210 1.0000 1.0000
0.000 0.0106 0.02041 0.01026 -0.0208 1.0000 1.0000
0.250 0.0291 0.02098 0.01072 -0.0206 1.0000 1.0000
0.500 0.0474 0.02162 0.01127 -0.0206 1.0000 1.0000
0.750 0.0654 0.02232 0.01189 -0.0206 1.0000 1.0000
1.000 0.0831 0.02310 0.01261 -0.0207 1.0000 1.0000
1.250 0.1321 0.02423 0.01368 -0.0266 0.9872 1.0000
1.500 0.1864 0.02532 0.01475 -0.0332 0.9693 1.0000
1.750 0.2382 0.02630 0.01573 -0.0390 0.9511 1.0000
2.000 0.2908 0.02718 0.01664 -0.0447 0.9333 1.0000
2.250 0.3334 0.02791 0.01743 -0.0483 0.9138 1.0000
2.500 0.3748 0.02858 0.01816 -0.0515 0.8943 1.0000
2.750 0.4197 0.02913 0.01881 -0.0550 0.8755 1.0000
3.000 0.4688 0.02950 0.01931 -0.0587 0.8576 1.0000
3.250 0.5023 0.02999 0.01992 -0.0599 0.8371 1.0000
3.500 0.5444 0.03022 0.02032 -0.0619 0.8175 1.0000
3.750 0.5894 0.03012 0.02040 -0.0637 0.7988 1.0000
4.000 0.6266 0.03010 0.02055 -0.0640 0.7788 1.0000
4.250 0.6587 0.03012 0.02073 -0.0635 0.7568 1.0000
4.500 0.7013 0.02942 0.02024 -0.0634 0.7365 1.0000
4.750 0.7289 0.02935 0.02032 -0.0616 0.7116 1.0000
5.000 0.7651 0.02851 0.01964 -0.0599 0.6867 1.0000
5.250 0.7983 0.02762 0.01887 -0.0575 0.6581 1.0000
5.500 0.8240 0.02715 0.01849 -0.0545 0.6249 1.0000
5.750 0.8494 0.02663 0.01800 -0.0514 0.5878 1.0000
6.000 0.8727 0.02611 0.01745 -0.0479 0.5444 1.0000
6.250 0.8928 0.02559 0.01673 -0.0440 0.4916 1.0000
6.500 0.9060 0.02563 0.01652 -0.0398 0.4266 1.0000
6.750 0.9147 0.02638 0.01679 -0.0354 0.3469 1.0000
7.000 0.9239 0.02807 0.01781 -0.0318 0.2731 1.0000
7.250 0.9416 0.03024 0.01958 -0.0298 0.2261 1.0000
7.500 0.9635 0.03234 0.02148 -0.0286 0.1977 1.0000
7.750 0.9877 0.03445 0.02348 -0.0277 0.1790 1.0000
8.000 1.0133 0.03694 0.02613 -0.0270 0.1677 1.0000
8.250 1.0379 0.03960 0.02887 -0.0264 0.1591 1.0000
8.500 1.0574 0.04201 0.03161 -0.0252 0.1505 1.0000
8.750 1.0762 0.04511 0.03495 -0.0241 0.1450 1.0000
9.000 1.0875 0.04859 0.03902 -0.0222 0.1421 1.0000
9.250 1.0964 0.05208 0.04295 -0.0203 0.1387 1.0000
9.500 1.1176 0.05544 0.04616 -0.0200 0.1327 1.0000
9.750 1.1145 0.05948 0.05081 -0.0174 0.1315 1.0000
10.000 1.1104 0.06405 0.05583 -0.0153 0.1314 1.0000
10.250 1.1007 0.06884 0.06100 -0.0133 0.1317 1.0000
10.500 1.0872 0.07378 0.06624 -0.0116 0.1320 1.0000
10.750 1.0720 0.07888 0.07155 -0.0103 0.1325 1.0000
11.000 0.9600 0.08957 0.08260 -0.0137 0.1430 1.0000
11.250 0.8907 0.10813 0.10107 -0.0274 0.1593 1.0000
11.500 0.8893 0.11454 0.10748 -0.0291 0.1610 1.0000
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Polar data table (+)
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