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NACA 2418 (naca2418-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2418 (naca2418-il)
Reynolds number: 50,000
Max Cl/Cd: 27.33 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2418-il-50000-n5.txt
Download as CSV file: xf-naca2418-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2418                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4996   0.10521   0.09626  -0.0490   1.0000   0.1228
 -12.250  -0.6177   0.08014   0.07111  -0.0630   1.0000   0.1272
 -12.000  -0.7343   0.06365   0.05429  -0.0702   1.0000   0.1271
 -11.750  -0.7835   0.05837   0.04879  -0.0684   1.0000   0.1278
 -11.500  -0.8231   0.05509   0.04531  -0.0637   1.0000   0.1287
 -11.250  -0.8345   0.05343   0.04364  -0.0599   1.0000   0.1306
 -11.000  -0.8308   0.05245   0.04273  -0.0572   1.0000   0.1332
 -10.750  -0.8390   0.05086   0.04108  -0.0536   1.0000   0.1358
 -10.500  -0.8519   0.04893   0.03897  -0.0494   1.0000   0.1385
 -10.250  -0.8667   0.04676   0.03648  -0.0449   1.0000   0.1414
 -10.000  -0.8578   0.04592   0.03575  -0.0425   1.0000   0.1446
  -9.750  -0.8535   0.04492   0.03474  -0.0396   1.0000   0.1482
  -9.500  -0.8542   0.04346   0.03309  -0.0363   1.0000   0.1524
  -9.250  -0.8512   0.04212   0.03161  -0.0333   1.0000   0.1564
  -9.000  -0.8415   0.04141   0.03097  -0.0309   1.0000   0.1605
  -8.750  -0.8354   0.04032   0.02975  -0.0283   1.0000   0.1655
  -8.500  -0.8281   0.03919   0.02847  -0.0258   1.0000   0.1705
  -8.250  -0.8167   0.03856   0.02792  -0.0236   1.0000   0.1753
  -8.000  -0.8074   0.03762   0.02682  -0.0213   1.0000   0.1814
  -7.750  -0.7956   0.03686   0.02604  -0.0193   1.0000   0.1870
  -7.500  -0.7831   0.03625   0.02543  -0.0174   1.0000   0.1932
  -7.250  -0.7688   0.03543   0.02444  -0.0159   0.9994   0.2006
  -7.000  -0.7331   0.03488   0.02394  -0.0182   0.9926   0.2101
  -6.750  -0.6996   0.03418   0.02317  -0.0202   0.9851   0.2204
  -6.500  -0.6648   0.03354   0.02235  -0.0223   0.9777   0.2329
  -6.250  -0.6311   0.03304   0.02195  -0.0240   0.9697   0.2439
  -6.000  -0.5980   0.03249   0.02137  -0.0256   0.9617   0.2567
  -5.750  -0.5636   0.03196   0.02076  -0.0275   0.9537   0.2714
  -5.500  -0.5329   0.03151   0.02032  -0.0285   0.9449   0.2857
  -5.250  -0.4977   0.03107   0.01993  -0.0303   0.9372   0.3012
  -5.000  -0.4686   0.03066   0.01954  -0.0309   0.9276   0.3167
  -4.750  -0.4331   0.03027   0.01916  -0.0327   0.9199   0.3345
  -4.500  -0.4051   0.02993   0.01883  -0.0330   0.9098   0.3517
  -4.250  -0.3694   0.02957   0.01851  -0.0346   0.9020   0.3715
  -4.000  -0.3420   0.02930   0.01828  -0.0348   0.8918   0.3904
  -3.750  -0.3067   0.02898   0.01803  -0.0362   0.8837   0.4120
  -3.500  -0.2789   0.02875   0.01787  -0.0362   0.8735   0.4331
  -3.250  -0.2447   0.02847   0.01769  -0.0373   0.8652   0.4569
  -3.000  -0.2154   0.02825   0.01756  -0.0375   0.8555   0.4808
  -2.750  -0.1835   0.02800   0.01738  -0.0380   0.8464   0.5072
  -2.500  -0.1541   0.02779   0.01725  -0.0380   0.8372   0.5339
  -2.250  -0.1256   0.02760   0.01717  -0.0376   0.8272   0.5602
  -2.000  -0.0951   0.02740   0.01705  -0.0376   0.8184   0.5888
  -1.750  -0.0689   0.02727   0.01698  -0.0369   0.8078   0.6178
  -1.500  -0.0363   0.02709   0.01690  -0.0369   0.7998   0.6464
  -1.250  -0.0117   0.02706   0.01695  -0.0357   0.7885   0.6745
  -1.000   0.0234   0.02686   0.01679  -0.0360   0.7814   0.7051
  -0.750   0.0465   0.02698   0.01699  -0.0344   0.7691   0.7316
  -0.500   0.0865   0.02679   0.01681  -0.0353   0.7629   0.7610
  -0.250   0.1072   0.02702   0.01707  -0.0336   0.7497   0.7882
   0.000   0.1516   0.02688   0.01692  -0.0352   0.7432   0.8139
   0.250   0.1790   0.02719   0.01725  -0.0347   0.7304   0.8386
   0.500   0.2272   0.02705   0.01704  -0.0373   0.7233   0.8621
   0.750   0.2603   0.02737   0.01736  -0.0380   0.7106   0.8854
   1.000   0.3142   0.02722   0.01711  -0.0418   0.7031   0.9055
   1.250   0.3553   0.02752   0.01739  -0.0444   0.6902   0.9261
   1.500   0.4169   0.02727   0.01703  -0.0499   0.6820   0.9421
   1.750   0.4622   0.02750   0.01726  -0.0536   0.6684   0.9601
   2.000   0.5150   0.02740   0.01710  -0.0584   0.6577   0.9754
   2.250   0.5658   0.02730   0.01697  -0.0629   0.6455   0.9898
   2.500   0.6053   0.02735   0.01699  -0.0658   0.6329   1.0000
   2.750   0.6247   0.02722   0.01676  -0.0644   0.6232   1.0000
   3.000   0.6320   0.02754   0.01707  -0.0614   0.6107   1.0000
   3.250   0.6533   0.02744   0.01686  -0.0601   0.6011   1.0000
   3.500   0.6611   0.02781   0.01723  -0.0570   0.5887   1.0000
   3.750   0.6787   0.02791   0.01726  -0.0552   0.5785   1.0000
   4.000   0.6924   0.02817   0.01748  -0.0529   0.5672   1.0000
   4.250   0.7074   0.02844   0.01772  -0.0507   0.5567   1.0000
   4.500   0.7251   0.02865   0.01789  -0.0488   0.5462   1.0000
   4.750   0.7382   0.02906   0.01828  -0.0464   0.5354   1.0000
   5.000   0.7587   0.02925   0.01841  -0.0450   0.5254   1.0000
   5.250   0.7700   0.02978   0.01895  -0.0423   0.5145   1.0000
   5.500   0.7929   0.02994   0.01904  -0.0412   0.5046   1.0000
   5.750   0.8019   0.03059   0.01973  -0.0383   0.4934   1.0000
   6.000   0.8276   0.03070   0.01977  -0.0375   0.4839   1.0000
   6.250   0.8340   0.03148   0.02061  -0.0343   0.4722   1.0000
   6.500   0.8616   0.03156   0.02059  -0.0338   0.4628   1.0000
   6.750   0.8664   0.03242   0.02155  -0.0305   0.4508   1.0000
   7.000   0.8868   0.03274   0.02184  -0.0291   0.4405   1.0000
   7.250   0.8993   0.03333   0.02246  -0.0268   0.4290   1.0000
   7.500   0.9119   0.03395   0.02309  -0.0245   0.4179   1.0000
   7.750   0.9337   0.03416   0.02325  -0.0233   0.4071   1.0000
   8.000   0.9377   0.03513   0.02429  -0.0201   0.3953   1.0000
   8.250   0.9579   0.03541   0.02452  -0.0187   0.3848   1.0000
   8.500   0.9629   0.03630   0.02546  -0.0157   0.3736   1.0000
   8.750   0.9737   0.03700   0.02618  -0.0134   0.3632   1.0000
   9.000   0.9873   0.03758   0.02674  -0.0114   0.3527   1.0000
   9.250   0.9904   0.03876   0.02798  -0.0086   0.3424   1.0000
   9.500   1.0116   0.03904   0.02819  -0.0074   0.3324   1.0000
   9.750   1.0072   0.04075   0.03004  -0.0043   0.3221   1.0000
  10.000   1.0263   0.04118   0.03038  -0.0031   0.3125   1.0000
  10.250   1.0226   0.04303   0.03236  -0.0005   0.3024   1.0000
  10.500   1.0353   0.04391   0.03321   0.0009   0.2930   1.0000
  10.750   1.0359   0.04563   0.03503   0.0029   0.2832   1.0000
  11.000   1.0421   0.04707   0.03648   0.0044   0.2741   1.0000
  11.250   1.0468   0.04862   0.03806   0.0059   0.2647   1.0000
  11.500   1.0467   0.05071   0.04022   0.0073   0.2559   1.0000
  11.750   1.0549   0.05206   0.04156   0.0085   0.2470   1.0000
  12.000   1.0493   0.05486   0.04447   0.0095   0.2386   1.0000
  12.250   1.0589   0.05616   0.04574   0.0105   0.2303   1.0000
  12.500   1.0496   0.05958   0.04928   0.0111   0.2224   1.0000
  12.750   1.0561   0.06131   0.05100   0.0119   0.2147   1.0000
  13.000   1.0475   0.06491   0.05471   0.0121   0.2075   1.0000
  13.250   1.0437   0.06801   0.05789   0.0122   0.2003   1.0000
  13.500   1.0447   0.07063   0.06054   0.0125   0.1938   1.0000
  13.750   1.0202   0.07676   0.06688   0.0113   0.1872   1.0000
  14.000   1.0461   0.07603   0.06599   0.0126   0.1811   1.0000
  14.250   0.9792   0.08902   0.07941   0.0081   0.1750   1.0000
  14.500   0.9941   0.08977   0.08012   0.0087   0.1694   1.0000
  14.750   0.8870   0.11219   0.10285  -0.0011   0.1604   1.0000
  15.000   0.9060   0.11208   0.10274  -0.0003   0.1563   1.0000
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