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CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.92 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkx-il-1000000-n5.txt
Download as CSV file: xf-clarkx-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK X AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6969   0.13016   0.12825  -0.0231   1.0000   0.0131
 -16.000  -1.1702   0.03799   0.03487  -0.0873   1.0000   0.0090
 -15.750  -1.1880   0.03307   0.02975  -0.0907   1.0000   0.0091
 -15.500  -1.1967   0.03055   0.02709  -0.0897   1.0000   0.0093
 -15.250  -1.1979   0.02872   0.02514  -0.0878   1.0000   0.0095
 -15.000  -1.1936   0.02718   0.02348  -0.0861   1.0000   0.0098
 -14.750  -1.1876   0.02590   0.02211  -0.0840   1.0000   0.0102
 -14.500  -1.1803   0.02481   0.02092  -0.0818   1.0000   0.0106
 -14.250  -1.1687   0.02381   0.01982  -0.0801   0.9996   0.0110
 -14.000  -1.1447   0.02259   0.01849  -0.0809   0.9976   0.0116
 -13.750  -1.1197   0.02144   0.01726  -0.0818   0.9956   0.0125
 -13.500  -1.0929   0.02048   0.01622  -0.0828   0.9941   0.0134
 -13.250  -1.0674   0.01967   0.01532  -0.0833   0.9915   0.0142
 -13.000  -1.0408   0.01887   0.01447  -0.0840   0.9891   0.0153
 -12.750  -1.0128   0.01819   0.01372  -0.0848   0.9869   0.0165
 -12.500  -0.9841   0.01758   0.01305  -0.0856   0.9849   0.0175
 -12.250  -0.9571   0.01701   0.01242  -0.0860   0.9818   0.0183
 -12.000  -0.9304   0.01651   0.01189  -0.0863   0.9780   0.0195
 -11.750  -0.9018   0.01607   0.01142  -0.0868   0.9749   0.0206
 -11.500  -0.8737   0.01566   0.01095  -0.0872   0.9717   0.0215
 -11.250  -0.8477   0.01528   0.01049  -0.0871   0.9666   0.0221
 -11.000  -0.8204   0.01488   0.01002  -0.0873   0.9622   0.0226
 -10.750  -0.7946   0.01441   0.00952  -0.0872   0.9573   0.0234
 -10.500  -0.7686   0.01406   0.00914  -0.0871   0.9515   0.0243
 -10.250  -0.7419   0.01375   0.00878  -0.0870   0.9463   0.0251
 -10.000  -0.7160   0.01345   0.00842  -0.0868   0.9403   0.0258
  -9.750  -0.6899   0.01315   0.00806  -0.0865   0.9338   0.0264
  -9.500  -0.6635   0.01287   0.00772  -0.0863   0.9278   0.0270
  -9.250  -0.6371   0.01262   0.00740  -0.0861   0.9208   0.0274
  -8.750  -0.5853   0.01191   0.00657  -0.0856   0.9066   0.0290
  -8.500  -0.5589   0.01165   0.00627  -0.0853   0.8994   0.0299
  -8.250  -0.5321   0.01141   0.00600  -0.0852   0.8918   0.0307
  -8.000  -0.5055   0.01116   0.00568  -0.0850   0.8841   0.0313
  -7.750  -0.4786   0.01093   0.00538  -0.0848   0.8761   0.0319
  -7.500  -0.4517   0.01071   0.00510  -0.0846   0.8682   0.0326
  -7.250  -0.4247   0.01049   0.00482  -0.0844   0.8596   0.0330
  -7.000  -0.3977   0.01029   0.00455  -0.0843   0.8515   0.0334
  -6.750  -0.3706   0.01008   0.00428  -0.0841   0.8427   0.0338
  -6.500  -0.3437   0.00981   0.00395  -0.0839   0.8346   0.0350
  -6.250  -0.3166   0.00961   0.00371  -0.0837   0.8258   0.0360
  -6.000  -0.2892   0.00943   0.00349  -0.0836   0.8177   0.0370
  -5.750  -0.2619   0.00928   0.00330  -0.0835   0.8090   0.0382
  -5.500  -0.2343   0.00914   0.00312  -0.0834   0.8008   0.0394
  -5.000  -0.1791   0.00889   0.00277  -0.0832   0.7839   0.0412
  -4.750  -0.1517   0.00874   0.00257  -0.0831   0.7757   0.0435
  -4.500  -0.1240   0.00860   0.00243  -0.0830   0.7673   0.0456
  -4.250  -0.0963   0.00850   0.00229  -0.0829   0.7593   0.0476
  -4.000  -0.0685   0.00841   0.00217  -0.0829   0.7509   0.0493
  -3.750  -0.0407   0.00832   0.00204  -0.0828   0.7429   0.0515
  -3.500  -0.0130   0.00821   0.00192  -0.0827   0.7344   0.0550
  -3.250   0.0148   0.00813   0.00182  -0.0827   0.7264   0.0581
  -3.000   0.0427   0.00807   0.00173  -0.0826   0.7174   0.0605
  -2.750   0.0704   0.00798   0.00164  -0.0826   0.7088   0.0660
  -2.250   0.1257   0.00788   0.00148  -0.0824   0.6875   0.0747
  -2.000   0.1533   0.00782   0.00141  -0.0823   0.6767   0.0817
  -1.750   0.1809   0.00777   0.00136  -0.0822   0.6664   0.0898
  -1.500   0.2085   0.00769   0.00130  -0.0821   0.6565   0.1050
  -1.250   0.2360   0.00760   0.00126  -0.0821   0.6469   0.1260
  -0.750   0.2911   0.00748   0.00119  -0.0819   0.6264   0.1627
  -0.500   0.3183   0.00738   0.00117  -0.0818   0.6160   0.1976
  -0.250   0.3452   0.00727   0.00117  -0.0817   0.6048   0.2504
   0.000   0.3727   0.00724   0.00118  -0.0816   0.5931   0.2755
   0.250   0.4002   0.00724   0.00119  -0.0815   0.5812   0.2945
   0.500   0.4274   0.00725   0.00121  -0.0814   0.5671   0.3155
   0.750   0.4540   0.00726   0.00124  -0.0811   0.5485   0.3465
   1.000   0.4798   0.00723   0.00129  -0.0808   0.5275   0.4053
   1.250   0.5053   0.00706   0.00135  -0.0805   0.5096   0.5070
   1.500   0.5304   0.00686   0.00142  -0.0801   0.4949   0.6212
   1.750   0.5546   0.00666   0.00151  -0.0794   0.4797   0.7363
   2.000   0.5793   0.00660   0.00161  -0.0787   0.4646   0.8063
   2.250   0.6024   0.00654   0.00172  -0.0775   0.4509   0.8830
   2.500   0.6282   0.00658   0.00183  -0.0768   0.4369   0.9409
   2.750   0.6614   0.00673   0.00194  -0.0780   0.4214   0.9684
   3.250   0.7296   0.00710   0.00215  -0.0809   0.3882   0.9931
   3.500   0.7660   0.00731   0.00228  -0.0829   0.3690   0.9998
   3.750   0.7904   0.00749   0.00240  -0.0822   0.3541   1.0000
   4.000   0.8145   0.00768   0.00252  -0.0815   0.3410   1.0000
   4.500   0.8635   0.00804   0.00279  -0.0802   0.3164   1.0000
   4.750   0.8882   0.00823   0.00293  -0.0796   0.3045   1.0000
   5.000   0.9124   0.00847   0.00310  -0.0790   0.2882   1.0000
   5.250   0.9361   0.00876   0.00330  -0.0783   0.2688   1.0000
   5.500   0.9599   0.00905   0.00350  -0.0776   0.2497   1.0000
   5.750   0.9826   0.00944   0.00375  -0.0768   0.2237   1.0000
   6.000   1.0058   0.00979   0.00400  -0.0760   0.2030   1.0000
   6.250   1.0288   0.01014   0.00426  -0.0753   0.1839   1.0000
   6.500   1.0521   0.01049   0.00452  -0.0745   0.1680   1.0000
   6.750   1.0758   0.01080   0.00478  -0.0739   0.1557   1.0000
   7.000   1.0988   0.01116   0.00507  -0.0731   0.1407   1.0000
   7.250   1.1196   0.01168   0.00544  -0.0721   0.1148   1.0000
   7.500   1.1373   0.01242   0.00597  -0.0706   0.0809   1.0000
   7.750   1.1547   0.01318   0.00656  -0.0690   0.0514   1.0000
   8.000   1.1730   0.01386   0.00712  -0.0675   0.0330   1.0000
   8.250   1.1939   0.01431   0.00755  -0.0665   0.0269   1.0000
   8.500   1.2152   0.01471   0.00795  -0.0655   0.0231   1.0000
   8.750   1.2361   0.01513   0.00836  -0.0645   0.0201   1.0000
   9.000   1.2563   0.01558   0.00880  -0.0634   0.0175   1.0000
   9.250   1.2755   0.01599   0.00923  -0.0621   0.0158   1.0000
   9.500   1.2939   0.01643   0.00968  -0.0606   0.0145   1.0000
   9.750   1.3113   0.01692   0.01018  -0.0591   0.0133   1.0000
  10.000   1.3289   0.01741   0.01070  -0.0576   0.0125   1.0000
  10.250   1.3465   0.01790   0.01122  -0.0561   0.0119   1.0000
  10.500   1.3633   0.01844   0.01180  -0.0547   0.0113   1.0000
  10.750   1.3793   0.01903   0.01241  -0.0531   0.0107   1.0000
  11.000   1.3942   0.01970   0.01311  -0.0515   0.0100   1.0000
  11.250   1.4087   0.02041   0.01385  -0.0499   0.0096   1.0000
  11.500   1.4239   0.02108   0.01457  -0.0484   0.0092   1.0000
  11.750   1.4384   0.02181   0.01535  -0.0469   0.0089   1.0000
  12.000   1.4520   0.02261   0.01620  -0.0454   0.0086   1.0000
  12.250   1.4648   0.02349   0.01713  -0.0439   0.0083   1.0000
  12.500   1.4768   0.02445   0.01813  -0.0424   0.0080   1.0000
  12.750   1.4878   0.02551   0.01924  -0.0409   0.0077   1.0000
  13.000   1.4971   0.02674   0.02052  -0.0394   0.0074   1.0000
  13.250   1.5057   0.02805   0.02189  -0.0379   0.0072   1.0000
  13.500   1.5155   0.02931   0.02322  -0.0366   0.0071   1.0000
  13.750   1.5244   0.03068   0.02466  -0.0354   0.0069   1.0000
  14.000   1.5324   0.03215   0.02621  -0.0343   0.0068   1.0000
  14.250   1.5397   0.03373   0.02786  -0.0332   0.0066   1.0000
  14.500   1.5461   0.03545   0.02965  -0.0322   0.0064   1.0000
  14.750   1.5518   0.03728   0.03155  -0.0313   0.0063   1.0000
  15.000   1.5563   0.03927   0.03360  -0.0305   0.0061   1.0000
  15.250   1.5597   0.04142   0.03583  -0.0297   0.0060   1.0000
  15.500   1.5619   0.04378   0.03827  -0.0291   0.0058   1.0000
  15.750   1.5628   0.04635   0.04092  -0.0287   0.0057   1.0000
  16.000   1.5623   0.04917   0.04382  -0.0284   0.0056   1.0000
  16.250   1.5597   0.05235   0.04709  -0.0282   0.0055   1.0000
  16.500   1.5553   0.05586   0.05070  -0.0283   0.0054   1.0000
  16.750   1.5484   0.05978   0.05473  -0.0286   0.0053   1.0000
  17.000   1.5440   0.06351   0.05856  -0.0291   0.0053   1.0000
  17.250   1.5386   0.06747   0.06263  -0.0297   0.0052   1.0000
  17.500   1.5319   0.07170   0.06697  -0.0306   0.0052   1.0000
  17.750   1.5241   0.07616   0.07153  -0.0316   0.0051   1.0000
  18.000   1.5143   0.08103   0.07652  -0.0328   0.0051   1.0000
  18.250   1.5038   0.08609   0.08169  -0.0343   0.0051   1.0000
  18.500   1.4920   0.09143   0.08714  -0.0359   0.0050   1.0000
  18.750   1.4795   0.09696   0.09278  -0.0377   0.0050   1.0000
  19.000   1.4659   0.10276   0.09870  -0.0398   0.0050   1.0000
  19.250   1.4522   0.10869   0.10474  -0.0420   0.0049   1.0000
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