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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 100,000
Max Cl/Cd: 63.71 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n6409-il-100000-n5.txt
Download as CSV file: xf-n6409-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2406   0.10188   0.09719  -0.0477   0.9816   0.0527
  -7.750  -0.2333   0.09956   0.09489  -0.0545   0.9733   0.0552
  -7.500  -0.2275   0.09698   0.09234  -0.0616   0.9624   0.0558
  -7.250  -0.2087   0.09270   0.08804  -0.0691   0.9551   0.0559
  -7.000  -0.1917   0.08852   0.08384  -0.0742   0.9476   0.0560
  -6.750  -0.1678   0.08359   0.07885  -0.0804   0.9432   0.0560
  -6.500  -0.1633   0.07847   0.07373  -0.0753   0.9370   0.0442
  -6.250  -0.1436   0.07454   0.06978  -0.0778   0.9318   0.0420
  -6.000  -0.1255   0.07042   0.06562  -0.0830   0.9232   0.0422
  -5.750  -0.0983   0.06553   0.06066  -0.0904   0.9168   0.0423
  -5.500  -0.0772   0.06110   0.05615  -0.0955   0.9081   0.0413
  -5.250  -0.0445   0.05539   0.05029  -0.1036   0.9023   0.0401
  -5.000  -0.0155   0.04985   0.04456  -0.1102   0.8946   0.0394
  -4.750   0.0204   0.04445   0.03888  -0.1171   0.8888   0.0405
  -4.500   0.0651   0.03726   0.03117  -0.1258   0.8857   0.0422
  -4.250   0.0916   0.03205   0.02535  -0.1287   0.8771   0.0426
  -4.000   0.1298   0.02747   0.01991  -0.1325   0.8732   0.0438
  -3.750   0.1622   0.02531   0.01728  -0.1340   0.8681   0.0466
  -3.500   0.1898   0.02427   0.01606  -0.1342   0.8608   0.0494
  -3.250   0.2259   0.02258   0.01394  -0.1358   0.8570   0.0524
  -3.000   0.2524   0.02143   0.01242  -0.1354   0.8489   0.0555
  -2.750   0.2853   0.02059   0.01154  -0.1364   0.8436   0.0611
  -2.500   0.3145   0.01984   0.01054  -0.1365   0.8365   0.0679
  -2.250   0.3449   0.01918   0.00989  -0.1369   0.8297   0.0765
  -2.000   0.3754   0.01862   0.00927  -0.1372   0.8229   0.0880
  -1.750   0.4046   0.01818   0.00877  -0.1373   0.8150   0.1023
  -1.500   0.4343   0.01778   0.00834  -0.1375   0.8074   0.1192
  -1.250   0.4643   0.01739   0.00793  -0.1377   0.7995   0.1384
  -1.000   0.4925   0.01709   0.00764  -0.1377   0.7906   0.1590
  -0.750   0.5240   0.01676   0.00731  -0.1381   0.7831   0.1859
  -0.500   0.5501   0.01657   0.00716  -0.1377   0.7729   0.2135
  -0.250   0.5817   0.01630   0.00691  -0.1382   0.7648   0.2509
   0.000   0.6102   0.01609   0.00676  -0.1382   0.7550   0.2961
   0.250   0.6383   0.01582   0.00665  -0.1382   0.7451   0.3638
   0.500   0.6737   0.01438   0.00645  -0.1393   0.7373   1.0000
   0.750   0.6997   0.01450   0.00639  -0.1387   0.7259   1.0000
   1.000   0.7274   0.01460   0.00633  -0.1385   0.7157   1.0000
   1.250   0.7570   0.01468   0.00623  -0.1387   0.7065   1.0000
   1.500   0.7831   0.01483   0.00627  -0.1382   0.6956   1.0000
   1.750   0.8099   0.01498   0.00632  -0.1379   0.6853   1.0000
   2.000   0.8383   0.01512   0.00632  -0.1379   0.6761   1.0000
   2.250   0.8641   0.01531   0.00646  -0.1374   0.6658   1.0000
   2.500   0.8903   0.01551   0.00659  -0.1370   0.6560   1.0000
   3.000   0.9430   0.01594   0.00691  -0.1363   0.6375   1.0000
   3.250   0.9694   0.01617   0.00709  -0.1360   0.6289   1.0000
   3.500   0.9953   0.01641   0.00730  -0.1356   0.6202   1.0000
   3.750   1.0205   0.01668   0.00757  -0.1351   0.6115   1.0000
   4.000   1.0471   0.01694   0.00781  -0.1349   0.6037   1.0000
   4.250   1.0712   0.01725   0.00816  -0.1342   0.5952   1.0000
   4.500   1.0981   0.01752   0.00841  -0.1340   0.5880   1.0000
   4.750   1.1214   0.01786   0.00885  -0.1332   0.5796   1.0000
   5.000   1.1482   0.01815   0.00913  -0.1330   0.5728   1.0000
   5.250   1.1708   0.01852   0.00961  -0.1322   0.5645   1.0000
   5.500   1.1974   0.01883   0.00993  -0.1319   0.5578   1.0000
   5.750   1.2194   0.01923   0.01048  -0.1310   0.5495   1.0000
   6.000   1.2456   0.01955   0.01085  -0.1306   0.5428   1.0000
   6.250   1.2669   0.01997   0.01142  -0.1296   0.5344   1.0000
   6.500   1.2929   0.02031   0.01180  -0.1292   0.5274   1.0000
   6.750   1.3129   0.02075   0.01245  -0.1279   0.5183   1.0000
   7.000   1.3345   0.02109   0.01290  -0.1267   0.5079   1.0000
   7.250   1.3499   0.02133   0.01318  -0.1243   0.4887   1.0000
   7.500   1.3622   0.02156   0.01338  -0.1212   0.4646   1.0000
   7.750   1.3721   0.02191   0.01377  -0.1179   0.4393   1.0000
   8.000   1.3818   0.02236   0.01428  -0.1147   0.4152   1.0000
   8.250   1.3881   0.02289   0.01482  -0.1110   0.3860   1.0000
   8.500   1.3900   0.02360   0.01543  -0.1066   0.3489   1.0000
   8.750   1.3885   0.02466   0.01627  -0.1020   0.3006   1.0000
   9.000   1.3808   0.02629   0.01753  -0.0970   0.2433   1.0000
   9.250   1.3688   0.02850   0.01933  -0.0921   0.1831   1.0000
   9.500   1.3573   0.03100   0.02148  -0.0878   0.1330   1.0000
   9.750   1.3481   0.03353   0.02380  -0.0842   0.0985   1.0000
  10.000   1.3421   0.03598   0.02614  -0.0812   0.0770   1.0000
  10.250   1.3381   0.03840   0.02853  -0.0786   0.0643   1.0000
  10.500   1.3355   0.04084   0.03102  -0.0763   0.0565   1.0000
  10.750   1.3321   0.04346   0.03370  -0.0743   0.0513   1.0000
  11.000   1.3293   0.04615   0.03649  -0.0726   0.0476   1.0000
  11.250   1.3279   0.04881   0.03930  -0.0711   0.0443   1.0000
  11.500   1.3252   0.05169   0.04228  -0.0699   0.0416   1.0000
  11.750   1.3205   0.05489   0.04553  -0.0687   0.0396   1.0000
  12.000   1.3219   0.05755   0.04836  -0.0678   0.0373   1.0000
  12.250   1.3225   0.06034   0.05131  -0.0670   0.0355   1.0000
  12.500   1.3235   0.06315   0.05423  -0.0662   0.0341   1.0000
  12.750   1.3250   0.06594   0.05709  -0.0655   0.0328   1.0000
  13.000   1.3274   0.06863   0.05983  -0.0647   0.0318   1.0000
  13.250   1.3346   0.07083   0.06210  -0.0637   0.0308   1.0000
  13.500   1.3433   0.07296   0.06441  -0.0628   0.0296   1.0000
  13.750   1.3510   0.07526   0.06687  -0.0621   0.0283   1.0000
  14.000   1.3572   0.07776   0.06954  -0.0617   0.0271   1.0000
  14.250   1.3635   0.08030   0.07219  -0.0612   0.0261   1.0000
  14.500   1.3711   0.08276   0.07476  -0.0607   0.0254   1.0000
  14.750   1.3801   0.08518   0.07726  -0.0601   0.0247   1.0000
  15.000   1.3881   0.08800   0.08024  -0.0595   0.0242   1.0000
  15.250   1.3890   0.09165   0.08419  -0.0595   0.0238   1.0000
  15.500   1.3861   0.09583   0.08868  -0.0600   0.0234   1.0000
  15.750   1.3802   0.10045   0.09359  -0.0610   0.0230   1.0000
  16.000   1.3721   0.10545   0.09887  -0.0624   0.0226   1.0000
  16.250   1.3623   0.11082   0.10452  -0.0642   0.0222   1.0000
  16.500   1.3511   0.11656   0.11051  -0.0666   0.0219   1.0000
  16.750   1.3387   0.12272   0.11692  -0.0694   0.0217   1.0000
  17.000   1.3246   0.12943   0.12387  -0.0729   0.0215   1.0000
  17.250   1.3086   0.13686   0.13154  -0.0771   0.0215   1.0000
  17.500   1.2903   0.14518   0.14009  -0.0822   0.0215   1.0000
  17.750   1.2691   0.15482   0.14996  -0.0885   0.0217   1.0000
  18.000   1.2442   0.16640   0.16174  -0.0963   0.0221   1.0000
  18.250   1.2160   0.18055   0.17603  -0.1059   0.0227   1.0000
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