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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 500,000
Max Cl/Cd: 87.51 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65410-il-500000-n5.txt
Download as CSV file: xf-naca65410-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4574   0.08633   0.08402  -0.0422   1.0000   0.0069
  -9.500  -0.4645   0.08114   0.07888  -0.0445   1.0000   0.0069
  -9.250  -0.4726   0.07614   0.07392  -0.0470   1.0000   0.0069
  -9.000  -0.4867   0.07053   0.06836  -0.0502   1.0000   0.0069
  -8.750  -0.4994   0.06306   0.06090  -0.0593   0.9911   0.0067
  -8.500  -0.4981   0.05329   0.05091  -0.0701   0.9783   0.0067
  -8.000  -0.5154   0.02055   0.01579  -0.0794   0.9496   0.0081
  -7.750  -0.4873   0.02035   0.01556  -0.0802   0.9424   0.0085
  -7.500  -0.4576   0.02039   0.01558  -0.0811   0.9364   0.0089
  -7.250  -0.4328   0.01913   0.01408  -0.0812   0.9280   0.0096
  -7.000  -0.4085   0.01735   0.01195  -0.0810   0.9203   0.0104
  -6.750  -0.3837   0.01604   0.01036  -0.0808   0.9121   0.0110
  -6.500  -0.3593   0.01485   0.00898  -0.0805   0.9044   0.0117
  -6.250  -0.3334   0.01434   0.00838  -0.0804   0.8967   0.0123
  -6.000  -0.3071   0.01407   0.00806  -0.0804   0.8893   0.0132
  -5.750  -0.2808   0.01366   0.00754  -0.0803   0.8819   0.0143
  -5.500  -0.2550   0.01312   0.00688  -0.0801   0.8744   0.0152
  -5.250  -0.2289   0.01263   0.00627  -0.0799   0.8673   0.0159
  -5.000  -0.2041   0.01179   0.00535  -0.0796   0.8601   0.0170
  -4.750  -0.1777   0.01146   0.00496  -0.0796   0.8531   0.0182
  -4.500  -0.1511   0.01116   0.00462  -0.0795   0.8460   0.0195
  -4.250  -0.1247   0.01078   0.00416  -0.0794   0.8390   0.0206
  -4.000  -0.0979   0.01044   0.00376  -0.0794   0.8324   0.0217
  -3.750  -0.0709   0.01019   0.00343  -0.0794   0.8258   0.0227
  -3.500  -0.0440   0.00979   0.00296  -0.0794   0.8194   0.0247
  -3.250  -0.0169   0.00950   0.00262  -0.0794   0.8126   0.0268
  -3.000   0.0106   0.00930   0.00236  -0.0795   0.8063   0.0291
  -2.750   0.0383   0.00913   0.00214  -0.0796   0.7999   0.0318
  -2.500   0.0659   0.00898   0.00193  -0.0796   0.7942   0.0360
  -2.250   0.0937   0.00880   0.00177  -0.0798   0.7878   0.0455
  -2.000   0.1212   0.00849   0.00161  -0.0800   0.7816   0.0998
  -1.750   0.1481   0.00769   0.00140  -0.0806   0.7756   0.2903
  -1.500   0.1742   0.00666   0.00132  -0.0812   0.7696   0.5808
  -1.250   0.2012   0.00650   0.00139  -0.0811   0.7642   0.6637
  -1.000   0.2289   0.00647   0.00141  -0.0810   0.7580   0.6913
  -0.750   0.2565   0.00648   0.00143  -0.0810   0.7524   0.7128
  -0.500   0.2845   0.00649   0.00144  -0.0810   0.7467   0.7270
  -0.250   0.3126   0.00650   0.00144  -0.0811   0.7408   0.7336
   0.000   0.3408   0.00653   0.00144  -0.0812   0.7354   0.7400
   0.250   0.3688   0.00655   0.00146  -0.0813   0.7295   0.7463
   0.750   0.4249   0.00661   0.00153  -0.0815   0.7182   0.7590
   1.000   0.4530   0.00664   0.00157  -0.0816   0.7124   0.7659
   1.250   0.4808   0.00668   0.00163  -0.0816   0.7070   0.7721
   1.500   0.5087   0.00672   0.00169  -0.0817   0.7000   0.7789
   1.750   0.5357   0.00677   0.00174  -0.0815   0.6859   0.7854
   2.000   0.5624   0.00685   0.00180  -0.0813   0.6698   0.7927
   2.250   0.5893   0.00692   0.00188  -0.0811   0.6565   0.7997
   2.500   0.6152   0.00703   0.00195  -0.0807   0.6317   0.8069
   2.750   0.6385   0.00730   0.00203  -0.0798   0.5789   0.8141
   3.000   0.6586   0.00786   0.00221  -0.0784   0.4828   0.8224
   3.250   0.6742   0.00898   0.00268  -0.0766   0.3350   0.8307
   3.500   0.6917   0.01005   0.00319  -0.0752   0.2058   0.8397
   3.750   0.7093   0.01104   0.00372  -0.0738   0.0939   0.8482
   4.000   0.7308   0.01166   0.00411  -0.0729   0.0445   0.8570
   4.250   0.7546   0.01198   0.00443  -0.0722   0.0337   0.8665
   4.500   0.7783   0.01224   0.00474  -0.0715   0.0298   0.8762
   4.750   0.8012   0.01259   0.00513  -0.0707   0.0255   0.8866
   5.250   0.8463   0.01321   0.00590  -0.0688   0.0215   0.9101
   5.500   0.8676   0.01353   0.00629  -0.0676   0.0198   0.9240
   6.250   0.9327   0.01497   0.00792  -0.0647   0.0159   1.0000
   6.500   0.9556   0.01553   0.00853  -0.0642   0.0154   1.0000
   6.750   0.9778   0.01613   0.00919  -0.0635   0.0148   1.0000
   7.000   0.9993   0.01679   0.00992  -0.0627   0.0143   1.0000
   7.250   1.0205   0.01747   0.01068  -0.0618   0.0138   1.0000
   7.500   1.0414   0.01819   0.01145  -0.0609   0.0133   1.0000
   7.750   1.0623   0.01886   0.01217  -0.0601   0.0128   1.0000
   8.000   1.0832   0.01951   0.01285  -0.0593   0.0122   1.0000
   8.250   1.1012   0.02055   0.01395  -0.0581   0.0116   1.0000
   8.500   1.1184   0.02198   0.01552  -0.0568   0.0112   1.0000
   8.750   1.1384   0.02292   0.01657  -0.0559   0.0109   1.0000
   9.000   1.1582   0.02388   0.01765  -0.0549   0.0106   1.0000
   9.250   1.1775   0.02484   0.01873  -0.0539   0.0102   1.0000
   9.500   1.1958   0.02581   0.01983  -0.0528   0.0097   1.0000
   9.750   1.2125   0.02670   0.02084  -0.0515   0.0093   1.0000
  10.000   1.2280   0.02773   0.02199  -0.0501   0.0089   1.0000
  10.250   1.2420   0.02874   0.02310  -0.0484   0.0087   1.0000
  10.500   1.2548   0.02968   0.02417  -0.0467   0.0084   1.0000
  10.750   1.2661   0.03081   0.02540  -0.0449   0.0082   1.0000
  11.000   1.2749   0.03222   0.02694  -0.0430   0.0079   1.0000
  11.250   1.2784   0.03473   0.02970  -0.0406   0.0076   1.0000
  11.500   1.2860   0.03628   0.03146  -0.0388   0.0074   1.0000
  11.750   1.2902   0.03832   0.03375  -0.0368   0.0071   1.0000
  12.000   1.2914   0.04067   0.03634  -0.0348   0.0068   1.0000
  12.250   1.2888   0.04343   0.03935  -0.0328   0.0065   1.0000
  12.500   1.2854   0.04619   0.04234  -0.0312   0.0063   1.0000
  12.750   1.2771   0.04963   0.04602  -0.0297   0.0061   1.0000
  13.000   1.2661   0.05348   0.05011  -0.0287   0.0060   1.0000
  13.250   1.2542   0.05760   0.05444  -0.0283   0.0059   1.0000
  13.500   1.2386   0.06247   0.05952  -0.0286   0.0058   1.0000
  13.750   1.2195   0.06822   0.06549  -0.0298   0.0058   1.0000
  14.000   1.1869   0.07678   0.07433  -0.0327   0.0058   1.0000
  14.250   1.1356   0.09042   0.08829  -0.0398   0.0059   1.0000
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