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N-9 (n9-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: N-9 (n9-il)
Reynolds number: 500,000
Max Cl/Cd: 78.27 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n9-il-500000-n5.txt
Download as CSV file: xf-n9-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7543   0.03596   0.03309  -0.0586   1.0000   0.0065
 -11.000  -0.7563   0.02944   0.02600  -0.0593   1.0000   0.0066
 -10.750  -0.7453   0.02620   0.02240  -0.0587   1.0000   0.0068
 -10.500  -0.7286   0.02425   0.02021  -0.0580   1.0000   0.0070
 -10.250  -0.7099   0.02274   0.01850  -0.0572   1.0000   0.0072
 -10.000  -0.6903   0.02142   0.01700  -0.0563   1.0000   0.0075
  -9.750  -0.6702   0.02019   0.01558  -0.0553   1.0000   0.0077
  -9.500  -0.6497   0.01903   0.01423  -0.0544   1.0000   0.0081
  -9.250  -0.6201   0.01786   0.01282  -0.0552   0.9980   0.0085
  -9.000  -0.5891   0.01688   0.01164  -0.0562   0.9957   0.0090
  -8.750  -0.5589   0.01576   0.01034  -0.0571   0.9929   0.0097
  -8.500  -0.5280   0.01500   0.00948  -0.0580   0.9891   0.0104
  -8.250  -0.4964   0.01435   0.00872  -0.0590   0.9856   0.0111
  -7.750  -0.4364   0.01312   0.00724  -0.0600   0.9737   0.0127
  -7.500  -0.4056   0.01249   0.00654  -0.0607   0.9676   0.0142
  -7.250  -0.3738   0.01216   0.00620  -0.0615   0.9611   0.0160
  -7.000  -0.3408   0.01177   0.00574  -0.0625   0.9545   0.0178
  -6.750  -0.3078   0.01130   0.00522  -0.0636   0.9480   0.0198
  -6.500  -0.2738   0.01103   0.00492  -0.0649   0.9413   0.0226
  -6.250  -0.2402   0.01079   0.00461  -0.0660   0.9339   0.0251
  -6.000  -0.2079   0.01044   0.00417  -0.0669   0.9258   0.0272
  -5.750  -0.1780   0.01011   0.00382  -0.0673   0.9171   0.0302
  -5.500  -0.1487   0.00991   0.00353  -0.0674   0.9089   0.0326
  -5.250  -0.1207   0.00974   0.00328  -0.0673   0.8986   0.0345
  -5.000  -0.0933   0.00955   0.00301  -0.0670   0.8873   0.0363
  -4.750  -0.0661   0.00932   0.00273  -0.0667   0.8754   0.0396
  -4.500  -0.0389   0.00914   0.00251  -0.0664   0.8631   0.0424
  -4.250  -0.0117   0.00899   0.00230  -0.0661   0.8488   0.0454
  -4.000   0.0154   0.00882   0.00212  -0.0658   0.8300   0.0536
  -3.750   0.0420   0.00869   0.00197  -0.0653   0.8012   0.0695
  -3.500   0.0679   0.00867   0.00182  -0.0647   0.7635   0.0820
  -3.250   0.0941   0.00870   0.00169  -0.0642   0.7342   0.0903
  -3.000   0.1209   0.00873   0.00160  -0.0638   0.7127   0.0975
  -2.750   0.1481   0.00872   0.00151  -0.0636   0.6962   0.1044
  -2.500   0.1758   0.00869   0.00144  -0.0635   0.6842   0.1131
  -2.000   0.2307   0.00838   0.00136  -0.0634   0.6651   0.2077
  -1.750   0.2584   0.00827   0.00133  -0.0634   0.6552   0.2442
  -1.500   0.2855   0.00805   0.00131  -0.0633   0.6417   0.3198
  -1.250   0.3119   0.00768   0.00133  -0.0633   0.6276   0.4646
  -1.000   0.3386   0.00747   0.00135  -0.0631   0.6139   0.5576
  -0.750   0.3647   0.00724   0.00137  -0.0628   0.5986   0.6537
  -0.500   0.3883   0.00693   0.00141  -0.0617   0.5783   0.7835
  -0.250   0.4159   0.00667   0.00146  -0.0610   0.5526   0.9661
   0.000   0.4515   0.00681   0.00146  -0.0628   0.5190   1.0000
   0.250   0.4771   0.00704   0.00150  -0.0624   0.4788   1.0000
   0.500   0.5022   0.00736   0.00159  -0.0619   0.4321   1.0000
   0.750   0.5275   0.00769   0.00171  -0.0615   0.3920   1.0000
   1.000   0.5534   0.00796   0.00184  -0.0612   0.3633   1.0000
   1.250   0.5798   0.00817   0.00196  -0.0610   0.3440   1.0000
   1.500   0.6062   0.00839   0.00208  -0.0608   0.3261   1.0000
   1.750   0.6328   0.00859   0.00222  -0.0606   0.3118   1.0000
   2.000   0.6596   0.00877   0.00235  -0.0605   0.2998   1.0000
   2.250   0.6863   0.00896   0.00250  -0.0604   0.2870   1.0000
   2.500   0.7128   0.00917   0.00266  -0.0602   0.2701   1.0000
   2.750   0.7389   0.00944   0.00283  -0.0600   0.2474   1.0000
   3.000   0.7644   0.00978   0.00302  -0.0597   0.2134   1.0000
   3.250   0.7863   0.01060   0.00343  -0.0591   0.1317   1.0000
   3.500   0.8115   0.01098   0.00374  -0.0588   0.1159   1.0000
   3.750   0.8371   0.01131   0.00404  -0.0585   0.1077   1.0000
   4.000   0.8633   0.01156   0.00430  -0.0583   0.1036   1.0000
   4.250   0.8893   0.01183   0.00460  -0.0581   0.0994   1.0000
   4.500   0.9148   0.01215   0.00491  -0.0579   0.0947   1.0000
   4.750   0.9402   0.01248   0.00526  -0.0576   0.0910   1.0000
   5.000   0.9662   0.01271   0.00554  -0.0574   0.0883   1.0000
   5.250   0.9917   0.01299   0.00586  -0.0572   0.0834   1.0000
   5.500   1.0166   0.01336   0.00620  -0.0569   0.0774   1.0000
   5.750   1.0424   0.01359   0.00648  -0.0568   0.0728   1.0000
   6.000   1.0672   0.01394   0.00680  -0.0565   0.0665   1.0000
   6.250   1.0922   0.01425   0.00715  -0.0563   0.0617   1.0000
   6.500   1.1165   0.01463   0.00751  -0.0559   0.0535   1.0000
   6.750   1.1402   0.01508   0.00793  -0.0555   0.0435   1.0000
   7.000   1.1625   0.01568   0.00846  -0.0549   0.0304   1.0000
   7.250   1.1824   0.01654   0.00923  -0.0540   0.0171   1.0000
   7.500   1.2033   0.01728   0.00999  -0.0532   0.0129   1.0000
   7.750   1.2253   0.01786   0.01064  -0.0525   0.0116   1.0000
   8.000   1.2462   0.01853   0.01141  -0.0517   0.0104   1.0000
   8.250   1.2658   0.01934   0.01229  -0.0507   0.0093   1.0000
   8.500   1.2853   0.02011   0.01316  -0.0497   0.0087   1.0000
   8.750   1.3050   0.02081   0.01396  -0.0488   0.0081   1.0000
   9.000   1.3237   0.02157   0.01481  -0.0478   0.0075   1.0000
   9.250   1.3414   0.02239   0.01571  -0.0466   0.0070   1.0000
   9.500   1.3568   0.02337   0.01677  -0.0452   0.0066   1.0000
   9.750   1.3686   0.02462   0.01813  -0.0433   0.0062   1.0000
  10.000   1.3824   0.02557   0.01922  -0.0417   0.0060   1.0000
  10.250   1.3924   0.02660   0.02037  -0.0395   0.0058   1.0000
  10.500   1.4004   0.02773   0.02162  -0.0372   0.0056   1.0000
  10.750   1.4071   0.02900   0.02301  -0.0349   0.0055   1.0000
  11.000   1.4126   0.03041   0.02455  -0.0328   0.0053   1.0000
  11.250   1.4167   0.03201   0.02628  -0.0309   0.0051   1.0000
  11.500   1.4199   0.03380   0.02819  -0.0293   0.0050   1.0000
  11.750   1.4224   0.03576   0.03027  -0.0279   0.0049   1.0000
  12.000   1.4235   0.03798   0.03261  -0.0269   0.0048   1.0000
  12.250   1.4233   0.04050   0.03526  -0.0262   0.0046   1.0000
  12.500   1.4208   0.04347   0.03837  -0.0260   0.0045   1.0000
  12.750   1.4159   0.04699   0.04202  -0.0263   0.0044   1.0000
  13.000   1.4072   0.05121   0.04641  -0.0271   0.0044   1.0000
  13.250   1.3955   0.05606   0.05141  -0.0284   0.0043   1.0000
  13.500   1.3854   0.06092   0.05642  -0.0299   0.0042   1.0000
  13.750   1.3747   0.06608   0.06174  -0.0318   0.0042   1.0000
  14.000   1.3621   0.07179   0.06762  -0.0341   0.0042   1.0000
  14.250   1.3486   0.07794   0.07392  -0.0368   0.0042   1.0000
  14.500   1.3331   0.08470   0.08083  -0.0399   0.0041   1.0000
  14.750   1.3169   0.09181   0.08809  -0.0432   0.0041   1.0000
  15.000   1.2987   0.09935   0.09577  -0.0467   0.0041   1.0000
  15.250   1.2803   0.10710   0.10365  -0.0503   0.0041   1.0000
  15.500   1.2615   0.11503   0.11171  -0.0541   0.0041   1.0000
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