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N-9 (n9-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 50,000
Max Cl/Cd: 38.32 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n9-il-50000-n5.txt
Download as CSV file: xf-n9-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-9                                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4756   0.12028   0.11312  -0.0126   1.0000   0.0982
 -10.750  -0.4784   0.11714   0.11006  -0.0154   1.0000   0.0987
 -10.500  -0.4790   0.11362   0.10661  -0.0178   1.0000   0.0989
 -10.250  -0.4785   0.10988   0.10294  -0.0199   1.0000   0.0990
  -9.750  -0.4699   0.09580   0.08886  -0.0254   1.0000   0.0580
  -9.500  -0.4656   0.09202   0.08513  -0.0257   1.0000   0.0572
  -9.250  -0.4632   0.08807   0.08124  -0.0271   1.0000   0.0563
  -9.000  -0.4607   0.08375   0.07697  -0.0296   1.0000   0.0554
  -8.750  -0.4580   0.07915   0.07241  -0.0327   1.0000   0.0547
  -8.500  -0.4548   0.07430   0.06757  -0.0358   1.0000   0.0540
  -8.250  -0.4507   0.06933   0.06256  -0.0389   1.0000   0.0538
  -8.000  -0.4453   0.06429   0.05744  -0.0417   1.0000   0.0543
  -7.750  -0.4383   0.05920   0.05217  -0.0441   1.0000   0.0553
  -7.500  -0.4293   0.05407   0.04676  -0.0460   1.0000   0.0562
  -7.250  -0.4176   0.04912   0.04140  -0.0473   1.0000   0.0569
  -7.000  -0.4030   0.04458   0.03636  -0.0479   1.0000   0.0575
  -6.750  -0.3865   0.04075   0.03205  -0.0480   1.0000   0.0593
  -6.500  -0.3689   0.03910   0.03039  -0.0472   1.0000   0.0635
  -6.250  -0.3490   0.03619   0.02699  -0.0469   1.0000   0.0671
  -6.000  -0.3271   0.03320   0.02336  -0.0465   1.0000   0.0698
  -5.750  -0.3061   0.03134   0.02126  -0.0459   1.0000   0.0752
  -5.500  -0.2836   0.02964   0.01922  -0.0451   1.0000   0.0806
  -5.250  -0.2593   0.02782   0.01683  -0.0443   1.0000   0.0846
  -5.000  -0.2371   0.02655   0.01552  -0.0437   1.0000   0.0915
  -4.750  -0.2131   0.02542   0.01403  -0.0428   1.0000   0.0995
  -4.500  -0.1897   0.02420   0.01281  -0.0421   1.0000   0.1056
  -4.250  -0.1656   0.02325   0.01162  -0.0413   1.0000   0.1139
  -4.000  -0.1418   0.02246   0.01079  -0.0407   1.0000   0.1276
  -3.750  -0.1180   0.02180   0.01024  -0.0404   1.0000   0.1467
  -3.500  -0.0941   0.02130   0.00981  -0.0401   1.0000   0.1726
  -3.250  -0.0697   0.02080   0.00946  -0.0400   1.0000   0.2192
  -3.000  -0.0443   0.01996   0.00913  -0.0403   1.0000   0.3097
  -2.750  -0.0204   0.01850   0.00909  -0.0397   0.9979   0.6030
  -2.500   0.0220   0.01784   0.00885  -0.0416   0.9863   1.0000
  -2.250   0.0627   0.01808   0.00870  -0.0447   0.9760   1.0000
  -2.000   0.1027   0.01831   0.00862  -0.0475   0.9653   1.0000
  -1.750   0.1414   0.01852   0.00856  -0.0501   0.9539   1.0000
  -1.500   0.1811   0.01870   0.00854  -0.0528   0.9417   1.0000
  -1.250   0.2261   0.01878   0.00842  -0.0561   0.9274   1.0000
  -1.000   0.2734   0.01875   0.00825  -0.0596   0.9123   1.0000
  -0.750   0.3164   0.01871   0.00808  -0.0622   0.8966   1.0000
  -0.500   0.3537   0.01874   0.00803  -0.0637   0.8814   1.0000
  -0.250   0.3852   0.01886   0.00809  -0.0642   0.8656   1.0000
   0.000   0.4150   0.01899   0.00818  -0.0644   0.8492   1.0000
   0.250   0.4441   0.01911   0.00828  -0.0644   0.8326   1.0000
   0.500   0.4730   0.01921   0.00837  -0.0642   0.8159   1.0000
   0.750   0.5021   0.01927   0.00843  -0.0641   0.7991   1.0000
   1.000   0.5315   0.01931   0.00847  -0.0638   0.7827   1.0000
   1.250   0.5590   0.01940   0.00859  -0.0633   0.7643   1.0000
   1.500   0.5870   0.01948   0.00868  -0.0628   0.7459   1.0000
   1.750   0.6153   0.01958   0.00879  -0.0622   0.7275   1.0000
   2.000   0.6437   0.01970   0.00893  -0.0617   0.7088   1.0000
   2.250   0.6696   0.01994   0.00920  -0.0609   0.6865   1.0000
   2.500   0.6960   0.02013   0.00938  -0.0599   0.6624   1.0000
   2.750   0.7204   0.02036   0.00965  -0.0587   0.6344   1.0000
   3.000   0.7438   0.02060   0.00988  -0.0574   0.6040   1.0000
   3.250   0.7665   0.02086   0.01015  -0.0560   0.5719   1.0000
   3.500   0.7891   0.02116   0.01047  -0.0547   0.5397   1.0000
   3.750   0.8116   0.02148   0.01080  -0.0534   0.5069   1.0000
   4.000   0.8334   0.02184   0.01109  -0.0520   0.4728   1.0000
   4.250   0.8550   0.02231   0.01146  -0.0507   0.4397   1.0000
   4.500   0.8763   0.02288   0.01202  -0.0495   0.4082   1.0000
   4.750   0.8968   0.02356   0.01265  -0.0483   0.3751   1.0000
   5.000   0.9166   0.02433   0.01338  -0.0470   0.3413   1.0000
   5.250   0.9355   0.02520   0.01422  -0.0457   0.3061   1.0000
   5.500   0.9535   0.02617   0.01519  -0.0444   0.2655   1.0000
   5.750   0.9711   0.02724   0.01623  -0.0431   0.2282   1.0000
   6.000   0.9889   0.02841   0.01728  -0.0418   0.2032   1.0000
   6.250   1.0078   0.02960   0.01848  -0.0407   0.1863   1.0000
   6.500   1.0265   0.03084   0.01972  -0.0397   0.1727   1.0000
   6.750   1.0450   0.03213   0.02101  -0.0386   0.1615   1.0000
   7.000   1.0655   0.03347   0.02250  -0.0377   0.1523   1.0000
   7.250   1.0855   0.03494   0.02415  -0.0368   0.1431   1.0000
   7.500   1.1055   0.03656   0.02576  -0.0359   0.1343   1.0000
   7.750   1.1249   0.03830   0.02778  -0.0350   0.1247   1.0000
   8.000   1.1408   0.04025   0.02993  -0.0339   0.1136   1.0000
   8.250   1.1519   0.04215   0.03195  -0.0325   0.1013   1.0000
   8.500   1.1603   0.04400   0.03388  -0.0309   0.0899   1.0000
   8.750   1.1667   0.04599   0.03620  -0.0290   0.0799   1.0000
   9.000   1.1716   0.04847   0.03904  -0.0270   0.0711   1.0000
   9.250   1.1766   0.05039   0.04100  -0.0253   0.0649   1.0000
   9.500   1.1740   0.05347   0.04461  -0.0228   0.0591   1.0000
   9.750   1.1724   0.05582   0.04713  -0.0208   0.0551   1.0000
  10.000   1.1722   0.05842   0.04975  -0.0193   0.0524   1.0000
  10.250   1.1622   0.06266   0.05447  -0.0179   0.0504   1.0000
  10.500   1.1495   0.06705   0.05921  -0.0173   0.0488   1.0000
  10.750   1.1346   0.07183   0.06428  -0.0175   0.0478   1.0000
  11.000   1.1170   0.07734   0.07004  -0.0189   0.0472   1.0000
  11.250   1.0954   0.08395   0.07690  -0.0215   0.0472   1.0000
  11.500   1.0691   0.09213   0.08528  -0.0256   0.0479   1.0000
  11.750   1.0398   0.10189   0.09520  -0.0313   0.0492   1.0000
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