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NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il)
Reynolds number: 500,000
Max Cl/Cd: 113.08 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652415a05-il-500000.txt
Download as CSV file: xf-naca652415a05-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415 a=0.5                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5943   0.04663   0.04299  -0.0826   0.8161   0.0216
 -10.500  -0.6151   0.04372   0.03987  -0.0789   0.8091   0.0215
 -10.250  -0.6334   0.04021   0.03599  -0.0754   0.8030   0.0216
 -10.000  -0.6406   0.03726   0.03266  -0.0725   0.7971   0.0217
  -9.750  -0.6485   0.03274   0.02767  -0.0696   0.7922   0.0220
  -9.500  -0.6318   0.03147   0.02639  -0.0692   0.7876   0.0227
  -9.250  -0.5990   0.03331   0.02854  -0.0702   0.7827   0.0237
  -9.000  -0.5934   0.02993   0.02473  -0.0680   0.7781   0.0238
  -8.750  -0.5808   0.02745   0.02189  -0.0664   0.7740   0.0241
  -8.500  -0.5637   0.02546   0.01962  -0.0653   0.7695   0.0247
  -8.250  -0.5442   0.02378   0.01765  -0.0644   0.7651   0.0254
  -8.000  -0.5225   0.02272   0.01632  -0.0636   0.7613   0.0261
  -7.750  -0.5012   0.02100   0.01434  -0.0630   0.7578   0.0271
  -7.500  -0.4769   0.01996   0.01327  -0.0628   0.7539   0.0279
  -7.250  -0.4521   0.01919   0.01244  -0.0626   0.7500   0.0287
  -7.000  -0.4270   0.01843   0.01160  -0.0624   0.7465   0.0295
  -6.750  -0.4018   0.01772   0.01075  -0.0621   0.7433   0.0304
  -6.500  -0.3760   0.01725   0.01019  -0.0619   0.7398   0.0316
  -6.250  -0.3501   0.01674   0.00959  -0.0617   0.7361   0.0323
  -6.000  -0.3266   0.01543   0.00826  -0.0612   0.7326   0.0334
  -5.750  -0.3020   0.01485   0.00766  -0.0609   0.7295   0.0345
  -5.500  -0.2770   0.01443   0.00718  -0.0606   0.7266   0.0357
  -5.250  -0.2513   0.01403   0.00677  -0.0604   0.7236   0.0372
  -5.000  -0.2254   0.01368   0.00638  -0.0602   0.7204   0.0385
  -4.750  -0.2011   0.01315   0.00580  -0.0598   0.7174   0.0397
  -4.500  -0.1772   0.01258   0.00521  -0.0593   0.7146   0.0417
  -4.250  -0.1514   0.01229   0.00487  -0.0591   0.7120   0.0438
  -4.000  -0.1249   0.01206   0.00462  -0.0590   0.7092   0.0464
  -3.750  -0.0992   0.01168   0.00423  -0.0588   0.7063   0.0499
  -3.500  -0.0726   0.01141   0.00396  -0.0588   0.7035   0.0547
  -3.250  -0.0461   0.01113   0.00368  -0.0587   0.7010   0.0641
  -3.000  -0.0229   0.01041   0.00335  -0.0583   0.6986   0.1556
  -2.750  -0.0072   0.00889   0.00295  -0.0572   0.6963   0.4516
  -2.500   0.0166   0.00850   0.00294  -0.0567   0.6939   0.5691
  -2.250   0.0434   0.00837   0.00295  -0.0566   0.6913   0.6153
  -2.000   0.0708   0.00832   0.00296  -0.0565   0.6887   0.6461
  -1.750   0.0989   0.00831   0.00295  -0.0566   0.6863   0.6677
  -1.500   0.1265   0.00829   0.00298  -0.0566   0.6842   0.6908
  -1.250   0.1534   0.00833   0.00307  -0.0563   0.6821   0.7224
  -1.000   0.1805   0.00843   0.00318  -0.0560   0.6800   0.7470
  -0.750   0.2082   0.00847   0.00326  -0.0560   0.6778   0.7603
  -0.500   0.2367   0.00848   0.00328  -0.0562   0.6755   0.7689
  -0.250   0.2651   0.00850   0.00331  -0.0564   0.6732   0.7760
   0.000   0.2938   0.00853   0.00332  -0.0567   0.6710   0.7839
   0.250   0.3222   0.00853   0.00335  -0.0569   0.6689   0.7907
   0.500   0.3510   0.00858   0.00336  -0.0572   0.6668   0.7990
   0.750   0.3793   0.00863   0.00342  -0.0574   0.6649   0.8060
   1.000   0.4077   0.00872   0.00351  -0.0576   0.6630   0.8141
   1.250   0.4356   0.00874   0.00359  -0.0578   0.6609   0.8214
   1.500   0.4636   0.00879   0.00367  -0.0580   0.6585   0.8298
   1.750   0.4916   0.00883   0.00376  -0.0581   0.6563   0.8374
   2.000   0.5197   0.00888   0.00383  -0.0582   0.6542   0.8457
   2.250   0.5477   0.00892   0.00390  -0.0584   0.6521   0.8533
   2.500   0.5758   0.00899   0.00398  -0.0585   0.6502   0.8619
   2.750   0.6035   0.00912   0.00412  -0.0586   0.6481   0.8698
   3.000   0.6303   0.00917   0.00426  -0.0585   0.6458   0.8787
   3.250   0.6569   0.00922   0.00440  -0.0584   0.6432   0.8868
   3.500   0.6838   0.00926   0.00449  -0.0583   0.6402   0.8963
   3.750   0.7104   0.00927   0.00453  -0.0581   0.6371   0.9045
   4.000   0.7378   0.00931   0.00456  -0.0580   0.6339   0.9138
   4.250   0.7624   0.00931   0.00466  -0.0574   0.6294   0.9231
   4.500   0.7877   0.00925   0.00466  -0.0568   0.6241   0.9329
   4.750   0.8139   0.00921   0.00463  -0.0565   0.6197   0.9435
   5.000   0.8398   0.00910   0.00459  -0.0560   0.6114   0.9536
   5.250   0.8683   0.00884   0.00433  -0.0561   0.5959   0.9634
   5.500   0.8997   0.00877   0.00428  -0.0570   0.5827   0.9725
   5.750   0.9358   0.00878   0.00431  -0.0589   0.5710   0.9787
   6.000   0.9716   0.00883   0.00439  -0.0609   0.5555   0.9853
   6.250   1.0087   0.00892   0.00453  -0.0633   0.5331   0.9907
   6.500   1.0420   0.00930   0.00473  -0.0652   0.4821   0.9992
   6.750   1.0367   0.01009   0.00516  -0.0597   0.4136   1.0000
   7.000   1.0286   0.01137   0.00600  -0.0541   0.3360   1.0000
   7.250   1.0187   0.01260   0.00688  -0.0482   0.2734   1.0000
   7.500   1.0067   0.01393   0.00791  -0.0425   0.2199   1.0000
   7.750   0.9982   0.01546   0.00916  -0.0379   0.1671   1.0000
   8.000   0.9922   0.01711   0.01052  -0.0341   0.1172   1.0000
   8.250   0.9881   0.01882   0.01197  -0.0308   0.0754   1.0000
   8.500   0.9883   0.02040   0.01338  -0.0281   0.0498   1.0000
   8.750   0.9953   0.02164   0.01457  -0.0263   0.0409   1.0000
   9.000   1.0051   0.02275   0.01568  -0.0247   0.0364   1.0000
   9.250   1.0134   0.02399   0.01694  -0.0231   0.0330   1.0000
   9.500   1.0248   0.02504   0.01803  -0.0219   0.0309   1.0000
   9.750   1.0326   0.02637   0.01937  -0.0205   0.0290   1.0000
  10.000   1.0389   0.02784   0.02088  -0.0189   0.0276   1.0000
  10.250   1.0498   0.02901   0.02211  -0.0178   0.0266   1.0000
  10.500   1.0600   0.03024   0.02338  -0.0167   0.0255   1.0000
  10.750   1.0684   0.03162   0.02481  -0.0155   0.0248   1.0000
  11.000   1.0758   0.03313   0.02633  -0.0144   0.0238   1.0000
  11.250   1.0817   0.03478   0.02802  -0.0131   0.0234   1.0000
  11.500   1.0870   0.03651   0.02981  -0.0118   0.0225   1.0000
  11.750   1.0975   0.03787   0.03122  -0.0109   0.0223   1.0000
  12.000   1.1083   0.03923   0.03265  -0.0102   0.0216   1.0000
  12.250   1.1189   0.04062   0.03409  -0.0094   0.0211   1.0000
  12.500   1.1294   0.04203   0.03556  -0.0087   0.0204   1.0000
  12.750   1.1399   0.04347   0.03704  -0.0079   0.0202   1.0000
  13.000   1.1503   0.04495   0.03855  -0.0073   0.0196   1.0000
  13.250   1.1607   0.04642   0.04005  -0.0065   0.0192   1.0000
  13.500   1.1723   0.04782   0.04147  -0.0057   0.0189   1.0000
  13.750   1.1890   0.04896   0.04266  -0.0045   0.0184   1.0000
  14.000   1.2001   0.05051   0.04431  -0.0040   0.0182   1.0000
  14.250   1.2120   0.05204   0.04595  -0.0035   0.0180   1.0000
  14.500   1.2232   0.05369   0.04773  -0.0030   0.0178   1.0000
  14.750   1.2325   0.05553   0.04969  -0.0025   0.0175   1.0000
  15.000   1.2408   0.05750   0.05178  -0.0021   0.0172   1.0000
  15.250   1.2485   0.05960   0.05400  -0.0018   0.0169   1.0000
  15.500   1.2546   0.06183   0.05636  -0.0015   0.0166   1.0000
  15.750   1.2597   0.06426   0.05891  -0.0013   0.0164   1.0000
  16.000   1.2636   0.06693   0.06172  -0.0012   0.0163   1.0000
  16.250   1.2651   0.06991   0.06485  -0.0011   0.0162   1.0000
  16.500   1.2669   0.07277   0.06784  -0.0013   0.0159   1.0000
  16.750   1.2656   0.07612   0.07133  -0.0016   0.0158   1.0000
  17.000   1.2627   0.07972   0.07507  -0.0021   0.0157   1.0000
  17.250   1.2578   0.08369   0.07919  -0.0029   0.0156   1.0000
  17.500   1.2493   0.08831   0.08399  -0.0039   0.0156   1.0000
  17.750   1.2436   0.09250   0.08830  -0.0051   0.0154   1.0000
  18.000   1.2233   0.09935   0.09543  -0.0073   0.0156   1.0000
  18.250   1.2042   0.10619   0.10251  -0.0099   0.0156   1.0000
  18.500   1.1840   0.11352   0.11006  -0.0133   0.0156   1.0000
  18.750   1.1127   0.13192   0.12902  -0.0231   0.0162   1.0000
  19.000   1.0468   0.15218   0.14965  -0.0355   0.0169   1.0000
  19.250   0.9645   0.18256   0.18029  -0.0533   0.0190   1.0000
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