Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 2414 (n2414-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2414 (n2414-il)
Reynolds number: 50,000
Max Cl/Cd: 29.23 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2414-il-50000.txt
Download as CSV file: xf-n2414-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2414                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3825   0.10398   0.09611  -0.0137   1.0000   0.3671
  -8.750  -0.5753   0.07718   0.06972  -0.0398   1.0000   0.1960
  -8.500  -0.5903   0.07225   0.06477  -0.0393   1.0000   0.1934
  -8.250  -0.6074   0.06745   0.05995  -0.0382   1.0000   0.1919
  -8.000  -0.6270   0.06252   0.05492  -0.0368   1.0000   0.1905
  -7.750  -0.6441   0.05772   0.04991  -0.0350   1.0000   0.1899
  -7.500  -0.6555   0.05323   0.04512  -0.0331   1.0000   0.1904
  -7.250  -0.6624   0.04905   0.04051  -0.0311   1.0000   0.1926
  -7.000  -0.6613   0.04554   0.03659  -0.0291   1.0000   0.1965
  -6.750  -0.6454   0.04405   0.03519  -0.0274   1.0000   0.2030
  -6.500  -0.6384   0.04119   0.03185  -0.0257   1.0000   0.2097
  -6.250  -0.6236   0.03937   0.02999  -0.0241   1.0000   0.2174
  -6.000  -0.6102   0.03731   0.02753  -0.0227   1.0000   0.2271
  -5.750  -0.5927   0.03593   0.02621  -0.0213   1.0000   0.2373
  -5.500  -0.5759   0.03426   0.02430  -0.0201   1.0000   0.2494
  -5.250  -0.5578   0.03290   0.02269  -0.0190   1.0000   0.2636
  -5.000  -0.5386   0.03183   0.02159  -0.0179   1.0000   0.2793
  -4.750  -0.5190   0.03079   0.02054  -0.0168   1.0000   0.2966
  -4.500  -0.4988   0.02984   0.01954  -0.0159   1.0000   0.3166
  -4.250  -0.4783   0.02903   0.01886  -0.0149   1.0000   0.3380
  -4.000  -0.4578   0.02831   0.01822  -0.0139   1.0000   0.3626
  -3.750  -0.4372   0.02761   0.01756  -0.0130   1.0000   0.3911
  -3.500  -0.4169   0.02705   0.01710  -0.0120   1.0000   0.4226
  -3.250  -0.3970   0.02657   0.01681  -0.0108   1.0000   0.4564
  -3.000  -0.3777   0.02618   0.01658  -0.0096   1.0000   0.4951
  -2.750  -0.3592   0.02588   0.01651  -0.0081   1.0000   0.5370
  -2.500  -0.3412   0.02566   0.01652  -0.0064   1.0000   0.5848
  -2.250  -0.3245   0.02550   0.01665  -0.0042   1.0000   0.6385
  -2.000  -0.3101   0.02540   0.01685  -0.0013   1.0000   0.7009
  -1.750  -0.2997   0.02540   0.01717   0.0029   1.0000   0.7715
  -1.500  -0.2877   0.02559   0.01766   0.0076   1.0000   0.8603
  -1.250  -0.1519   0.02739   0.01916  -0.0120   1.0000   1.0000
  -1.000  -0.1758   0.02659   0.01821  -0.0080   1.0000   1.0000
  -0.750  -0.1385   0.02713   0.01845  -0.0129   0.9894   1.0000
  -0.500  -0.0886   0.02800   0.01903  -0.0193   0.9742   1.0000
  -0.250  -0.0411   0.02885   0.01964  -0.0247   0.9589   1.0000
   0.000   0.0025   0.02963   0.02024  -0.0292   0.9437   1.0000
   0.250   0.0438   0.03037   0.02083  -0.0330   0.9283   1.0000
   0.500   0.0823   0.03109   0.02141  -0.0362   0.9130   1.0000
   0.750   0.1194   0.03177   0.02199  -0.0389   0.8977   1.0000
   1.000   0.1561   0.03245   0.02258  -0.0414   0.8829   1.0000
   1.250   0.1948   0.03309   0.02314  -0.0441   0.8685   1.0000
   1.500   0.2417   0.03363   0.02363  -0.0478   0.8553   1.0000
   1.750   0.2685   0.03426   0.02421  -0.0483   0.8396   1.0000
   2.000   0.2953   0.03492   0.02484  -0.0488   0.8243   1.0000
   2.250   0.3233   0.03559   0.02549  -0.0494   0.8094   1.0000
   2.500   0.3545   0.03620   0.02609  -0.0503   0.7950   1.0000
   2.750   0.3943   0.03658   0.02648  -0.0522   0.7817   1.0000
   3.000   0.4365   0.03678   0.02672  -0.0541   0.7682   1.0000
   3.250   0.4573   0.03753   0.02748  -0.0533   0.7525   1.0000
   3.500   0.4806   0.03823   0.02820  -0.0528   0.7371   1.0000
   3.750   0.5071   0.03883   0.02883  -0.0525   0.7221   1.0000
   4.000   0.5409   0.03909   0.02915  -0.0529   0.7078   1.0000
   4.250   0.5998   0.03799   0.02815  -0.0552   0.6966   1.0000
   4.500   0.6204   0.03863   0.02883  -0.0538   0.6804   1.0000
   4.750   0.6428   0.03918   0.02943  -0.0526   0.6642   1.0000
   5.000   0.6673   0.03960   0.02992  -0.0514   0.6480   1.0000
   5.250   0.6945   0.03980   0.03020  -0.0503   0.6318   1.0000
   5.500   0.7239   0.03981   0.03029  -0.0493   0.6155   1.0000
   5.750   0.7558   0.03958   0.03014  -0.0482   0.5989   1.0000
   6.000   0.7890   0.03919   0.02982  -0.0472   0.5816   1.0000
   6.250   0.8223   0.03873   0.02944  -0.0460   0.5635   1.0000
   6.500   0.8565   0.03815   0.02892  -0.0449   0.5444   1.0000
   6.750   0.8937   0.03732   0.02812  -0.0439   0.5243   1.0000
   7.000   0.9352   0.03621   0.02695  -0.0432   0.5031   1.0000
   7.250   0.9530   0.03668   0.02748  -0.0409   0.4805   1.0000
   7.500   0.9764   0.03673   0.02755  -0.0389   0.4568   1.0000
   7.750   1.0137   0.03591   0.02654  -0.0381   0.4319   1.0000
   8.000   1.0253   0.03674   0.02746  -0.0352   0.4073   1.0000
   8.250   1.0584   0.03624   0.02671  -0.0341   0.3811   1.0000
   8.500   1.0672   0.03731   0.02788  -0.0311   0.3569   1.0000
   8.750   1.0937   0.03742   0.02772  -0.0297   0.3315   1.0000
   9.000   1.1041   0.03868   0.02903  -0.0270   0.3093   1.0000
   9.250   1.1186   0.03981   0.03013  -0.0247   0.2878   1.0000
   9.500   1.1374   0.04093   0.03110  -0.0231   0.2679   1.0000
   9.750   1.1553   0.04233   0.03239  -0.0215   0.2502   1.0000
  10.000   1.1663   0.04414   0.03427  -0.0193   0.2353   1.0000
  10.250   1.1720   0.04640   0.03671  -0.0167   0.2231   1.0000
  10.500   1.1824   0.04855   0.03893  -0.0148   0.2118   1.0000
  10.750   1.2032   0.05045   0.04070  -0.0140   0.2002   1.0000
  11.000   1.1903   0.05362   0.04432  -0.0101   0.1944   1.0000
  11.250   1.2121   0.05568   0.04627  -0.0095   0.1848   1.0000
  11.500   1.1884   0.05944   0.05048  -0.0052   0.1821   1.0000
  11.750   1.1605   0.06334   0.05468  -0.0012   0.1802   1.0000
  12.000   1.1237   0.06835   0.05995   0.0018   0.1799   1.0000
  12.250   1.0714   0.07576   0.06761   0.0025   0.1818   1.0000
  12.500   1.0139   0.08592   0.07793  -0.0001   0.1844   1.0000
<< Back to NACA 2414 (n2414-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2414 (n2414-il)