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N-9 (n9-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 500,000
Max Cl/Cd: 84.04 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n9-il-500000.txt
Download as CSV file: xf-n9-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5413   0.04603   0.04351  -0.0490   1.0000   0.0184
  -8.750  -0.5500   0.03531   0.03223  -0.0501   1.0000   0.0176
  -8.500  -0.5501   0.02803   0.02421  -0.0492   1.0000   0.0177
  -8.250  -0.5401   0.02408   0.01967  -0.0476   1.0000   0.0180
  -8.000  -0.5284   0.02050   0.01567  -0.0459   1.0000   0.0187
  -7.750  -0.5103   0.01957   0.01465  -0.0445   1.0000   0.0193
  -7.500  -0.4829   0.01865   0.01359  -0.0448   0.9990   0.0202
  -7.250  -0.4493   0.01754   0.01227  -0.0462   0.9971   0.0216
  -7.000  -0.4141   0.01697   0.01151  -0.0476   0.9952   0.0231
  -6.750  -0.3822   0.01486   0.00916  -0.0489   0.9935   0.0248
  -6.500  -0.3487   0.01419   0.00844  -0.0501   0.9906   0.0264
  -6.250  -0.3140   0.01356   0.00771  -0.0515   0.9878   0.0285
  -6.000  -0.2779   0.01325   0.00731  -0.0531   0.9854   0.0304
  -5.750  -0.2447   0.01188   0.00588  -0.0545   0.9830   0.0337
  -5.500  -0.2121   0.01140   0.00536  -0.0554   0.9781   0.0364
  -5.250  -0.1755   0.01107   0.00498  -0.0571   0.9743   0.0389
  -5.000  -0.1401   0.01019   0.00407  -0.0587   0.9698   0.0431
  -4.750  -0.1060   0.00981   0.00368  -0.0599   0.9622   0.0469
  -4.500  -0.0713   0.00942   0.00324  -0.0611   0.9543   0.0507
  -4.250  -0.0356   0.00900   0.00285  -0.0626   0.9457   0.0582
  -4.000  -0.0021   0.00869   0.00256  -0.0636   0.9347   0.0716
  -3.750   0.0293   0.00844   0.00235  -0.0641   0.9219   0.0943
  -3.500   0.0581   0.00829   0.00216  -0.0641   0.9079   0.1093
  -3.250   0.0853   0.00815   0.00201  -0.0637   0.8924   0.1237
  -3.000   0.1116   0.00794   0.00189  -0.0632   0.8762   0.1570
  -2.750   0.1379   0.00770   0.00182  -0.0628   0.8603   0.2288
  -2.500   0.1642   0.00740   0.00172  -0.0625   0.8433   0.2981
  -2.250   0.1888   0.00672   0.00166  -0.0620   0.8215   0.4980
  -2.000   0.2121   0.00614   0.00161  -0.0610   0.7967   0.6796
  -1.750   0.2290   0.00557   0.00164  -0.0578   0.7730   0.8937
  -1.500   0.2753   0.00559   0.00159  -0.0613   0.7509   0.9906
  -1.250   0.3093   0.00572   0.00154  -0.0626   0.7294   1.0000
  -1.000   0.3349   0.00586   0.00153  -0.0620   0.7126   1.0000
  -0.750   0.3608   0.00598   0.00153  -0.0615   0.6971   1.0000
  -0.500   0.3869   0.00609   0.00155  -0.0610   0.6814   1.0000
  -0.250   0.4132   0.00620   0.00157  -0.0606   0.6675   1.0000
   0.000   0.4398   0.00629   0.00160  -0.0603   0.6539   1.0000
   0.250   0.4664   0.00639   0.00163  -0.0599   0.6395   1.0000
   0.500   0.4930   0.00649   0.00167  -0.0596   0.6239   1.0000
   0.750   0.5196   0.00659   0.00171  -0.0593   0.6050   1.0000
   1.000   0.5458   0.00673   0.00175  -0.0589   0.5788   1.0000
   1.250   0.5719   0.00689   0.00181  -0.0585   0.5489   1.0000
   1.500   0.5975   0.00711   0.00188  -0.0580   0.5068   1.0000
   1.750   0.6220   0.00747   0.00199  -0.0575   0.4530   1.0000
   2.000   0.6469   0.00784   0.00216  -0.0570   0.4104   1.0000
   2.250   0.6723   0.00817   0.00234  -0.0566   0.3794   1.0000
   2.500   0.6980   0.00848   0.00253  -0.0563   0.3545   1.0000
   2.750   0.7242   0.00873   0.00271  -0.0561   0.3355   1.0000
   3.000   0.7503   0.00899   0.00291  -0.0559   0.3170   1.0000
   3.250   0.7763   0.00926   0.00311  -0.0557   0.2953   1.0000
   3.500   0.8020   0.00957   0.00331  -0.0554   0.2638   1.0000
   3.750   0.8252   0.01021   0.00360  -0.0548   0.1892   1.0000
   4.000   0.8469   0.01107   0.00411  -0.0541   0.1314   1.0000
   4.250   0.8717   0.01151   0.00451  -0.0537   0.1208   1.0000
   4.500   0.8966   0.01193   0.00493  -0.0533   0.1138   1.0000
   4.750   0.9219   0.01229   0.00532  -0.0530   0.1090   1.0000
   5.000   0.9454   0.01287   0.00587  -0.0525   0.1018   1.0000
   5.250   0.9716   0.01308   0.00614  -0.0523   0.0974   1.0000
   5.500   0.9967   0.01342   0.00649  -0.0521   0.0921   1.0000
   5.750   1.0205   0.01391   0.00700  -0.0516   0.0867   1.0000
   6.000   1.0467   0.01410   0.00725  -0.0515   0.0826   1.0000
   6.250   1.0717   0.01441   0.00757  -0.0512   0.0776   1.0000
   6.500   1.0964   0.01476   0.00796  -0.0509   0.0726   1.0000
   6.750   1.1223   0.01495   0.00817  -0.0508   0.0663   1.0000
   7.000   1.1472   0.01525   0.00849  -0.0506   0.0588   1.0000
   7.250   1.1712   0.01566   0.00882  -0.0503   0.0450   1.0000
   7.500   1.1912   0.01655   0.00959  -0.0493   0.0290   1.0000
   7.750   1.2112   0.01742   0.01047  -0.0483   0.0234   1.0000
   8.000   1.2309   0.01829   0.01137  -0.0473   0.0204   1.0000
   8.250   1.2491   0.01928   0.01246  -0.0460   0.0187   1.0000
   8.500   1.2684   0.02009   0.01337  -0.0449   0.0175   1.0000
   8.750   1.2864   0.02100   0.01436  -0.0437   0.0165   1.0000
   9.000   1.3016   0.02213   0.01556  -0.0422   0.0155   1.0000
   9.250   1.3093   0.02394   0.01749  -0.0397   0.0145   1.0000
   9.500   1.3260   0.02478   0.01846  -0.0384   0.0140   1.0000
   9.750   1.3397   0.02585   0.01964  -0.0367   0.0134   1.0000
  10.000   1.3499   0.02704   0.02095  -0.0346   0.0130   1.0000
  10.250   1.3572   0.02829   0.02232  -0.0321   0.0125   1.0000
  10.500   1.3632   0.02967   0.02379  -0.0297   0.0122   1.0000
  10.750   1.3677   0.03123   0.02546  -0.0274   0.0119   1.0000
  11.000   1.3700   0.03306   0.02740  -0.0253   0.0116   1.0000
  11.250   1.3691   0.03535   0.02981  -0.0233   0.0113   1.0000
  11.500   1.3645   0.03822   0.03283  -0.0213   0.0111   1.0000
  11.750   1.3559   0.04179   0.03661  -0.0196   0.0109   1.0000
  12.000   1.3523   0.04482   0.03983  -0.0187   0.0108   1.0000
  12.250   1.3504   0.04774   0.04293  -0.0184   0.0107   1.0000
  12.500   1.3467   0.05107   0.04645  -0.0186   0.0106   1.0000
  12.750   1.3413   0.05480   0.05035  -0.0193   0.0104   1.0000
  13.000   1.3339   0.05900   0.05473  -0.0203   0.0103   1.0000
  13.250   1.3244   0.06364   0.05955  -0.0218   0.0102   1.0000
  13.500   1.3133   0.06874   0.06484  -0.0237   0.0102   1.0000
  13.750   1.3000   0.07445   0.07071  -0.0261   0.0101   1.0000
  14.000   1.2851   0.08070   0.07714  -0.0290   0.0100   1.0000
  14.250   1.2688   0.08760   0.08421  -0.0325   0.0100   1.0000
  14.500   1.2506   0.09520   0.09198  -0.0365   0.0100   1.0000
  14.750   1.2316   0.10328   0.10022  -0.0408   0.0101   1.0000
  15.000   1.2109   0.11200   0.10910  -0.0456   0.0101   1.0000
  15.250   1.1886   0.12132   0.11857  -0.0507   0.0102   1.0000
  15.500   1.1652   0.13132   0.12872  -0.0563   0.0103   1.0000
  15.750   1.1381   0.14277   0.14031  -0.0627   0.0105   1.0000
  16.000   1.1043   0.15665   0.15430  -0.0703   0.0108   1.0000
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