NACA 2412 (naca2412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 50,000 Max Cl/Cd: 32.54 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2412-il-50000.txt Download as CSV file: xf-naca2412-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2412
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4124 0.09868 0.09109 -0.0085 1.0000 0.3526
-8.250 -0.4121 0.09574 0.08821 -0.0081 1.0000 0.3645
-7.750 -0.5569 0.07132 0.06409 -0.0348 1.0000 0.1944
-7.500 -0.5864 0.06278 0.05529 -0.0376 1.0000 0.1791
-7.250 -0.5842 0.05855 0.05097 -0.0368 1.0000 0.1769
-7.000 -0.5854 0.05412 0.04630 -0.0361 1.0000 0.1759
-6.750 -0.5839 0.04991 0.04175 -0.0352 1.0000 0.1761
-6.500 -0.5787 0.04598 0.03741 -0.0342 1.0000 0.1769
-6.250 -0.5695 0.04233 0.03327 -0.0332 1.0000 0.1780
-6.000 -0.5571 0.03904 0.02937 -0.0321 1.0000 0.1801
-5.750 -0.5390 0.03725 0.02771 -0.0308 1.0000 0.1865
-5.500 -0.5221 0.03502 0.02500 -0.0297 1.0000 0.1945
-5.250 -0.5027 0.03319 0.02312 -0.0286 1.0000 0.2026
-5.000 -0.4827 0.03140 0.02102 -0.0277 1.0000 0.2144
-4.750 -0.4620 0.03000 0.01947 -0.0267 1.0000 0.2296
-4.500 -0.4411 0.02879 0.01829 -0.0256 1.0000 0.2477
-4.250 -0.4199 0.02773 0.01724 -0.0246 1.0000 0.2698
-4.000 -0.3983 0.02669 0.01619 -0.0237 1.0000 0.2964
-3.750 -0.3765 0.02576 0.01532 -0.0228 1.0000 0.3281
-3.500 -0.3545 0.02487 0.01462 -0.0218 1.0000 0.3646
-3.250 -0.3320 0.02402 0.01394 -0.0209 1.0000 0.4107
-3.000 -0.3108 0.02326 0.01352 -0.0195 1.0000 0.4653
-2.750 -0.2902 0.02263 0.01326 -0.0179 1.0000 0.5330
-2.500 -0.2718 0.02208 0.01312 -0.0155 1.0000 0.6126
-2.250 -0.2578 0.02160 0.01314 -0.0116 1.0000 0.7057
-2.000 -0.2485 0.02133 0.01336 -0.0057 1.0000 0.8198
-1.750 -0.1469 0.02166 0.01342 -0.0186 1.0000 1.0000
-1.500 -0.1502 0.02143 0.01292 -0.0162 1.0000 1.0000
-1.250 -0.1389 0.02160 0.01282 -0.0154 1.0000 1.0000
-1.000 -0.1244 0.02191 0.01290 -0.0148 1.0000 1.0000
-0.750 -0.1086 0.02233 0.01312 -0.0144 1.0000 1.0000
-0.500 -0.0922 0.02284 0.01344 -0.0142 1.0000 1.0000
-0.250 -0.0756 0.02341 0.01387 -0.0140 1.0000 1.0000
0.000 -0.0589 0.02406 0.01437 -0.0139 1.0000 1.0000
0.250 -0.0109 0.02515 0.01529 -0.0196 0.9880 1.0000
0.500 0.0450 0.02630 0.01630 -0.0263 0.9727 1.0000
0.750 0.0927 0.02724 0.01713 -0.0315 0.9559 1.0000
1.000 0.1375 0.02810 0.01792 -0.0359 0.9390 1.0000
1.250 0.1811 0.02891 0.01867 -0.0399 0.9222 1.0000
1.500 0.2231 0.02966 0.01938 -0.0434 0.9055 1.0000
1.750 0.2633 0.03035 0.02005 -0.0464 0.8888 1.0000
2.000 0.3025 0.03099 0.02069 -0.0491 0.8722 1.0000
2.250 0.3408 0.03158 0.02130 -0.0514 0.8557 1.0000
2.500 0.3785 0.03212 0.02188 -0.0534 0.8391 1.0000
2.750 0.4157 0.03261 0.02241 -0.0552 0.8227 1.0000
3.000 0.4528 0.03304 0.02290 -0.0568 0.8062 1.0000
3.250 0.4905 0.03336 0.02329 -0.0582 0.7897 1.0000
3.500 0.5281 0.03358 0.02359 -0.0593 0.7732 1.0000
3.750 0.5639 0.03371 0.02382 -0.0598 0.7566 1.0000
4.000 0.5990 0.03375 0.02396 -0.0600 0.7398 1.0000
4.250 0.6342 0.03367 0.02400 -0.0599 0.7228 1.0000
4.500 0.6700 0.03344 0.02387 -0.0596 0.7056 1.0000
4.750 0.7067 0.03304 0.02359 -0.0591 0.6881 1.0000
5.000 0.7429 0.03256 0.02322 -0.0583 0.6701 1.0000
5.250 0.7613 0.03315 0.02391 -0.0562 0.6481 1.0000
5.500 0.7935 0.03277 0.02364 -0.0549 0.6273 1.0000
5.750 0.8345 0.03161 0.02252 -0.0537 0.6057 1.0000
6.000 0.8567 0.03159 0.02258 -0.0512 0.5785 1.0000
6.250 0.8858 0.03097 0.02197 -0.0490 0.5498 1.0000
6.500 0.9139 0.03048 0.02143 -0.0468 0.5195 1.0000
6.750 0.9384 0.03029 0.02118 -0.0444 0.4869 1.0000
7.000 0.9598 0.03027 0.02111 -0.0418 0.4512 1.0000
7.250 0.9816 0.03017 0.02079 -0.0391 0.4122 1.0000
7.500 0.9960 0.03062 0.02110 -0.0360 0.3698 1.0000
7.750 1.0111 0.03129 0.02146 -0.0330 0.3273 1.0000
8.000 1.0252 0.03245 0.02238 -0.0304 0.2889 1.0000
8.250 1.0412 0.03394 0.02364 -0.0282 0.2576 1.0000
8.500 1.0592 0.03571 0.02527 -0.0266 0.2334 1.0000
8.750 1.0779 0.03769 0.02726 -0.0252 0.2149 1.0000
9.000 1.0969 0.03979 0.02940 -0.0239 0.2003 1.0000
9.250 1.1165 0.04201 0.03167 -0.0229 0.1886 1.0000
9.500 1.1354 0.04445 0.03424 -0.0217 0.1797 1.0000
9.750 1.1471 0.04737 0.03747 -0.0200 0.1731 1.0000
10.000 1.1591 0.04997 0.04031 -0.0183 0.1663 1.0000
10.250 1.1743 0.05308 0.04351 -0.0172 0.1611 1.0000
10.500 1.1677 0.05686 0.04785 -0.0142 0.1591 1.0000
10.750 1.1563 0.06085 0.05228 -0.0113 0.1573 1.0000
11.000 1.1391 0.06510 0.05688 -0.0084 0.1562 1.0000
11.250 1.1121 0.06964 0.06171 -0.0054 0.1562 1.0000
11.500 1.0760 0.07509 0.06736 -0.0035 0.1575 1.0000
11.750 1.0357 0.08206 0.07449 -0.0039 0.1595 1.0000
12.000 1.0001 0.09021 0.08272 -0.0064 0.1613 1.0000
12.250 0.8261 0.12916 0.12142 -0.0343 0.1942 1.0000
12.500 0.8419 0.13272 0.12503 -0.0334 0.1921 1.0000
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Polar data table (+)
Polar graphs
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