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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 500,000
Max Cl/Cd: 122.39 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6409-il-500000.txt
Download as CSV file: xf-n6409-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA6409 9%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2522   0.11576   0.11348  -0.0491   0.9935   0.0189
 -10.000  -0.2425   0.11172   0.10945  -0.0543   0.9908   0.0191
  -9.750  -0.2293   0.10767   0.10539  -0.0587   0.9885   0.0191
  -9.500  -0.2163   0.10266   0.10039  -0.0619   0.9868   0.0193
  -9.250  -0.1967   0.09925   0.09697  -0.0638   0.9855   0.0197
  -9.000  -0.1764   0.09606   0.09377  -0.0671   0.9843   0.0204
  -8.750  -0.1622   0.09278   0.09049  -0.0701   0.9800   0.0209
  -8.500  -0.1446   0.08914   0.08684  -0.0743   0.9765   0.0217
  -8.250  -0.0373   0.06404   0.06183  -0.0927   0.9634   0.0247
  -8.000  -0.0154   0.06166   0.05944  -0.0939   0.9617   0.0259
  -7.750   0.0009   0.05786   0.05564  -0.0976   0.9595   0.0269
  -7.500   0.0128   0.05404   0.05181  -0.1011   0.9548   0.0282
  -7.250   0.0165   0.04931   0.04707  -0.1085   0.9450   0.0302
  -7.000   0.0248   0.04531   0.04306  -0.1130   0.9354   0.0303
  -6.750   0.0308   0.03888   0.03659  -0.1185   0.9281   0.0309
  -6.500   0.0419   0.03708   0.03478  -0.1177   0.9194   0.0316
  -6.250   0.0578   0.03452   0.03218  -0.1196   0.9126   0.0324
  -6.000   0.0714   0.03193   0.02955  -0.1216   0.9034   0.0338
  -5.750   0.0880   0.02806   0.02560  -0.1264   0.8949   0.0357
  -5.500   0.1019   0.01927   0.01518  -0.1556   0.9026   0.0265
  -5.250   0.1256   0.01639   0.01177  -0.1558   0.8962   0.0269
  -5.000   0.1507   0.01493   0.01000  -0.1556   0.8893   0.0277
  -4.750   0.1785   0.01396   0.00877  -0.1557   0.8835   0.0290
  -4.500   0.2040   0.01326   0.00787  -0.1551   0.8758   0.0300
  -4.250   0.2320   0.01218   0.00652  -0.1552   0.8700   0.0308
  -4.000   0.2563   0.01121   0.00544  -0.1545   0.8618   0.0322
  -3.750   0.2846   0.01077   0.00490  -0.1545   0.8553   0.0338
  -3.500   0.3103   0.01045   0.00452  -0.1540   0.8465   0.0359
  -3.250   0.3380   0.01019   0.00415  -0.1538   0.8389   0.0379
  -3.000   0.3637   0.00958   0.00348  -0.1533   0.8302   0.0413
  -2.750   0.3907   0.00936   0.00321  -0.1530   0.8218   0.0455
  -2.500   0.4175   0.00905   0.00286  -0.1527   0.8130   0.0524
  -2.250   0.4438   0.00887   0.00264  -0.1522   0.8031   0.0620
  -2.000   0.4706   0.00875   0.00248  -0.1519   0.7937   0.0726
  -1.750   0.4972   0.00863   0.00233  -0.1515   0.7837   0.0851
  -1.500   0.5234   0.00852   0.00223  -0.1511   0.7732   0.0992
  -1.250   0.5497   0.00844   0.00213  -0.1507   0.7626   0.1155
  -1.000   0.5758   0.00836   0.00206  -0.1503   0.7515   0.1362
  -0.750   0.6017   0.00831   0.00202  -0.1498   0.7397   0.1589
  -0.500   0.6275   0.00826   0.00200  -0.1494   0.7279   0.1842
  -0.250   0.6533   0.00823   0.00199  -0.1489   0.7159   0.2125
   0.000   0.6788   0.00822   0.00200  -0.1484   0.7034   0.2459
   0.250   0.7041   0.00821   0.00201  -0.1478   0.6909   0.2839
   0.500   0.7291   0.00816   0.00205  -0.1473   0.6783   0.3392
   0.750   0.7444   0.00715   0.00224  -0.1449   0.6658   0.8025
   1.250   0.8106   0.00717   0.00228  -0.1470   0.6399   1.0000
   1.500   0.8356   0.00732   0.00234  -0.1464   0.6276   1.0000
   1.750   0.8605   0.00748   0.00240  -0.1458   0.6160   1.0000
   2.000   0.8854   0.00765   0.00248  -0.1451   0.6048   1.0000
   2.250   0.9106   0.00780   0.00257  -0.1446   0.5939   1.0000
   2.500   0.9357   0.00796   0.00267  -0.1440   0.5842   1.0000
   2.750   0.9606   0.00815   0.00278  -0.1434   0.5748   1.0000
   3.000   0.9860   0.00829   0.00291  -0.1430   0.5659   1.0000
   3.250   1.0109   0.00849   0.00304  -0.1424   0.5580   1.0000
   3.500   1.0363   0.00863   0.00318  -0.1419   0.5498   1.0000
   3.750   1.0613   0.00884   0.00333  -0.1414   0.5427   1.0000
   4.000   1.0866   0.00898   0.00349  -0.1409   0.5352   1.0000
   4.250   1.1114   0.00920   0.00366  -0.1404   0.5287   1.0000
   4.500   1.1367   0.00934   0.00384  -0.1399   0.5218   1.0000
   4.750   1.1614   0.00955   0.00403  -0.1394   0.5153   1.0000
   5.000   1.1864   0.00971   0.00422  -0.1389   0.5087   1.0000
   5.250   1.2105   0.00992   0.00441  -0.1382   0.5010   1.0000
   5.500   1.2337   0.01008   0.00460  -0.1373   0.4905   1.0000
   5.750   1.2548   0.01028   0.00478  -0.1360   0.4749   1.0000
   6.000   1.2748   0.01052   0.00496  -0.1345   0.4566   1.0000
   6.250   1.2957   0.01076   0.00517  -0.1332   0.4409   1.0000
   6.500   1.3174   0.01098   0.00540  -0.1321   0.4275   1.0000
   6.750   1.3383   0.01123   0.00565  -0.1309   0.4123   1.0000
   7.000   1.3575   0.01153   0.00593  -0.1293   0.3925   1.0000
   7.250   1.3744   0.01194   0.00624  -0.1273   0.3655   1.0000
   7.500   1.3864   0.01250   0.00665  -0.1245   0.3269   1.0000
   7.750   1.3920   0.01342   0.00727  -0.1206   0.2753   1.0000
   8.000   1.3922   0.01472   0.00819  -0.1160   0.2089   1.0000
   8.250   1.3886   0.01630   0.00934  -0.1111   0.1395   1.0000
   8.500   1.3855   0.01789   0.01058  -0.1064   0.0841   1.0000
   8.750   1.3865   0.01927   0.01174  -0.1024   0.0518   1.0000
   9.000   1.3918   0.02044   0.01285  -0.0992   0.0370   1.0000
   9.250   1.3987   0.02154   0.01396  -0.0963   0.0305   1.0000
   9.500   1.4075   0.02256   0.01502  -0.0938   0.0273   1.0000
   9.750   1.4099   0.02403   0.01655  -0.0906   0.0247   1.0000
  10.000   1.4198   0.02505   0.01766  -0.0885   0.0236   1.0000
  10.250   1.4275   0.02626   0.01895  -0.0862   0.0224   1.0000
  10.500   1.4343   0.02757   0.02033  -0.0840   0.0215   1.0000
  10.750   1.4390   0.02909   0.02191  -0.0818   0.0204   1.0000
  11.000   1.4376   0.03117   0.02407  -0.0791   0.0196   1.0000
  11.250   1.4348   0.03348   0.02650  -0.0766   0.0188   1.0000
  11.500   1.4400   0.03521   0.02833  -0.0749   0.0185   1.0000
  11.750   1.4431   0.03720   0.03041  -0.0733   0.0181   1.0000
  12.000   1.4468   0.03920   0.03251  -0.0718   0.0176   1.0000
  12.250   1.4492   0.04140   0.03481  -0.0704   0.0172   1.0000
  12.500   1.4515   0.04369   0.03719  -0.0691   0.0168   1.0000
  12.750   1.4539   0.04604   0.03962  -0.0680   0.0164   1.0000
  13.000   1.4568   0.04841   0.04206  -0.0670   0.0160   1.0000
  13.250   1.4590   0.05092   0.04466  -0.0661   0.0156   1.0000
  13.500   1.4599   0.05362   0.04741  -0.0653   0.0152   1.0000
  13.750   1.4581   0.05667   0.05055  -0.0641   0.0147   1.0000
  14.000   1.4613   0.05926   0.05324  -0.0631   0.0143   1.0000
  14.250   1.4665   0.06166   0.05577  -0.0626   0.0141   1.0000
  14.500   1.4713   0.06415   0.05838  -0.0621   0.0138   1.0000
  14.750   1.4755   0.06677   0.06112  -0.0617   0.0135   1.0000
  15.000   1.4796   0.06945   0.06393  -0.0613   0.0133   1.0000
  15.250   1.4828   0.07230   0.06691  -0.0611   0.0130   1.0000
  15.500   1.4851   0.07530   0.07004  -0.0610   0.0127   1.0000
  15.750   1.4868   0.07841   0.07326  -0.0612   0.0124   1.0000
  16.000   1.4872   0.08176   0.07673  -0.0616   0.0121   1.0000
  16.250   1.4872   0.08522   0.08029  -0.0621   0.0118   1.0000
  16.500   1.4868   0.08874   0.08390  -0.0628   0.0116   1.0000
  16.750   1.4862   0.09234   0.08758  -0.0633   0.0113   1.0000
  17.000   1.4823   0.09665   0.09204  -0.0637   0.0110   1.0000
  17.250   1.4697   0.10267   0.09832  -0.0647   0.0108   1.0000
  17.500   1.4604   0.10796   0.10381  -0.0667   0.0108   1.0000
  17.750   1.4502   0.11357   0.10961  -0.0691   0.0107   1.0000
  18.000   1.4390   0.11956   0.11579  -0.0719   0.0107   1.0000
  18.250   1.4269   0.12585   0.12227  -0.0749   0.0106   1.0000
  18.500   1.4139   0.13253   0.12915  -0.0784   0.0106   1.0000
  18.750   1.3994   0.13970   0.13651  -0.0824   0.0105   1.0000
  19.000   1.3842   0.14726   0.14425  -0.0869   0.0105   1.0000
  19.250   1.3678   0.15537   0.15254  -0.0919   0.0105   1.0000
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