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NACA 2412 (naca2412-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
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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