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CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 200,000
Max Cl/Cd: 76.22 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkx-il-200000.txt
Download as CSV file: xf-clarkx-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3905   0.08981   0.08619  -0.0420   1.0000   0.0817
  -8.750  -0.4207   0.08638   0.08290  -0.0437   1.0000   0.0845
  -8.500  -0.4586   0.08433   0.08099  -0.0416   1.0000   0.0850
  -8.250  -0.4969   0.08125   0.07799  -0.0415   1.0000   0.0853
  -8.000  -0.5389   0.07545   0.07203  -0.0454   0.9989   0.0858
  -7.750  -0.5213   0.07030   0.06699  -0.0456   0.9967   0.0873
  -7.500  -0.4931   0.07001   0.06676  -0.0434   0.9948   0.0891
  -7.250  -0.5029   0.04610   0.04170  -0.0639   0.9834   0.0747
  -7.000  -0.4817   0.04087   0.03619  -0.0659   0.9773   0.0695
  -6.750  -0.4576   0.03490   0.02959  -0.0689   0.9725   0.0683
  -6.500  -0.4301   0.03069   0.02479  -0.0709   0.9680   0.0682
  -6.250  -0.4019   0.02834   0.02201  -0.0719   0.9620   0.0699
  -6.000  -0.3665   0.02624   0.01946  -0.0740   0.9586   0.0715
  -5.750  -0.3275   0.02470   0.01750  -0.0765   0.9562   0.0728
  -5.500  -0.3029   0.02268   0.01527  -0.0765   0.9489   0.0748
  -5.250  -0.2662   0.02164   0.01418  -0.0786   0.9452   0.0779
  -5.000  -0.2261   0.02064   0.01305  -0.0812   0.9427   0.0809
  -4.500  -0.1590   0.01884   0.01094  -0.0834   0.9323   0.0873
  -4.250  -0.1205   0.01800   0.01017  -0.0857   0.9291   0.0926
  -4.000  -0.0809   0.01734   0.00941  -0.0878   0.9266   0.0982
  -3.750  -0.0552   0.01664   0.00875  -0.0874   0.9185   0.1036
  -3.500  -0.0204   0.01615   0.00826  -0.0887   0.9140   0.1120
  -3.250   0.0156   0.01545   0.00762  -0.0902   0.9107   0.1219
  -3.000   0.0396   0.01506   0.00726  -0.0893   0.9017   0.1327
  -2.750   0.0721   0.01447   0.00676  -0.0901   0.8969   0.1506
  -2.500   0.0983   0.01395   0.00638  -0.0897   0.8894   0.1787
  -2.250   0.1261   0.01327   0.00610  -0.0897   0.8828   0.2555
  -2.000   0.1537   0.01276   0.00589  -0.0895   0.8766   0.3439
  -1.750   0.1784   0.01233   0.00574  -0.0888   0.8682   0.4188
  -1.500   0.2047   0.01173   0.00556  -0.0882   0.8624   0.5278
  -1.250   0.2236   0.01116   0.00558  -0.0859   0.8529   0.6805
  -1.000   0.2509   0.01068   0.00556  -0.0842   0.8477   0.8535
  -0.750   0.2988   0.01063   0.00555  -0.0873   0.8393   0.9479
  -0.500   0.3639   0.01046   0.00524  -0.0944   0.8338   0.9902
  -0.250   0.4046   0.01039   0.00507  -0.0970   0.8240   1.0000
   0.000   0.4301   0.01033   0.00489  -0.0963   0.8152   1.0000
   0.250   0.4535   0.01034   0.00481  -0.0954   0.8044   1.0000
   0.500   0.4775   0.01037   0.00476  -0.0945   0.7941   1.0000
   0.750   0.5038   0.01035   0.00462  -0.0939   0.7854   1.0000
   1.000   0.5270   0.01041   0.00463  -0.0929   0.7738   1.0000
   1.250   0.5515   0.01046   0.00461  -0.0920   0.7633   1.0000
   1.500   0.5777   0.01049   0.00453  -0.0914   0.7538   1.0000
   1.750   0.6013   0.01056   0.00457  -0.0904   0.7417   1.0000
   2.000   0.6256   0.01063   0.00459  -0.0895   0.7300   1.0000
   2.250   0.6505   0.01070   0.00459  -0.0887   0.7184   1.0000
   2.500   0.6755   0.01075   0.00456  -0.0879   0.7057   1.0000
   2.750   0.6998   0.01082   0.00456  -0.0869   0.6918   1.0000
   3.000   0.7236   0.01091   0.00462  -0.0859   0.6775   1.0000
   3.250   0.7477   0.01101   0.00469  -0.0850   0.6635   1.0000
   3.500   0.7720   0.01113   0.00477  -0.0842   0.6495   1.0000
   3.750   0.7964   0.01126   0.00487  -0.0833   0.6350   1.0000
   4.000   0.8207   0.01140   0.00498  -0.0824   0.6202   1.0000
   4.250   0.8449   0.01156   0.00510  -0.0816   0.6051   1.0000
   4.500   0.8689   0.01173   0.00524  -0.0807   0.5891   1.0000
   4.750   0.8926   0.01192   0.00539  -0.0798   0.5720   1.0000
   5.000   0.9161   0.01213   0.00555  -0.0788   0.5543   1.0000
   5.250   0.9393   0.01238   0.00574  -0.0778   0.5363   1.0000
   5.500   0.9623   0.01264   0.00598  -0.0768   0.5176   1.0000
   5.750   0.9848   0.01292   0.00623  -0.0758   0.4980   1.0000
   6.000   1.0070   0.01324   0.00651  -0.0746   0.4781   1.0000
   6.250   1.0287   0.01361   0.00681  -0.0735   0.4581   1.0000
   6.500   1.0498   0.01397   0.00714  -0.0722   0.4361   1.0000
   6.750   1.0699   0.01439   0.00747  -0.0708   0.4131   1.0000
   7.000   1.0890   0.01482   0.00783  -0.0693   0.3877   1.0000
   7.250   1.1071   0.01532   0.00823  -0.0676   0.3626   1.0000
   7.500   1.1253   0.01581   0.00865  -0.0661   0.3383   1.0000
   7.750   1.1433   0.01635   0.00911  -0.0645   0.3167   1.0000
   8.000   1.1615   0.01686   0.00960  -0.0630   0.2957   1.0000
   8.250   1.1786   0.01742   0.01011  -0.0613   0.2752   1.0000
   8.500   1.1956   0.01799   0.01065  -0.0597   0.2560   1.0000
   8.750   1.2123   0.01855   0.01121  -0.0580   0.2353   1.0000
   9.000   1.2257   0.01925   0.01184  -0.0559   0.2120   1.0000
   9.250   1.2352   0.02011   0.01257  -0.0532   0.1774   1.0000
   9.750   1.2259   0.02410   0.01568  -0.0448   0.0655   1.0000
  10.000   1.2286   0.02574   0.01728  -0.0418   0.0556   1.0000
  10.250   1.2344   0.02719   0.01879  -0.0394   0.0503   1.0000
  10.500   1.2354   0.02902   0.02065  -0.0367   0.0468   1.0000
  10.750   1.2415   0.03054   0.02228  -0.0347   0.0441   1.0000
  11.000   1.2452   0.03232   0.02412  -0.0327   0.0419   1.0000
  11.250   1.2450   0.03447   0.02632  -0.0306   0.0404   1.0000
  11.500   1.2445   0.03680   0.02867  -0.0285   0.0391   1.0000
  11.750   1.2513   0.03856   0.03055  -0.0270   0.0379   1.0000
  12.000   1.2576   0.04041   0.03250  -0.0256   0.0366   1.0000
  12.250   1.2637   0.04231   0.03446  -0.0243   0.0352   1.0000
  12.500   1.2696   0.04427   0.03643  -0.0230   0.0339   1.0000
  12.750   1.2789   0.04624   0.03835  -0.0214   0.0327   1.0000
  13.000   1.2914   0.04803   0.04022  -0.0199   0.0320   1.0000
  13.250   1.3013   0.04988   0.04223  -0.0188   0.0314   1.0000
  13.500   1.3111   0.05185   0.04435  -0.0176   0.0308   1.0000
  13.750   1.3198   0.05397   0.04661  -0.0165   0.0301   1.0000
  14.000   1.3266   0.05623   0.04902  -0.0155   0.0294   1.0000
  14.250   1.3325   0.05853   0.05143  -0.0146   0.0287   1.0000
  14.500   1.3371   0.06097   0.05399  -0.0139   0.0280   1.0000
  14.750   1.3443   0.06344   0.05653  -0.0131   0.0274   1.0000
  15.000   1.3545   0.06637   0.05956  -0.0122   0.0268   1.0000
  15.250   1.3571   0.07021   0.06359  -0.0113   0.0266   1.0000
  15.500   1.3512   0.07440   0.06800  -0.0108   0.0265   1.0000
  15.750   1.3394   0.07855   0.07238  -0.0108   0.0265   1.0000
  16.000   1.3267   0.08301   0.07708  -0.0112   0.0265   1.0000
  16.250   1.3133   0.08783   0.08210  -0.0119   0.0265   1.0000
  16.500   1.2984   0.09274   0.08725  -0.0131   0.0265   1.0000
  16.750   1.2816   0.09799   0.09271  -0.0150   0.0266   1.0000
  17.000   1.2639   0.10365   0.09859  -0.0177   0.0267   1.0000
  17.250   1.2441   0.11009   0.10526  -0.0213   0.0269   1.0000
  17.500   1.2181   0.11826   0.11370  -0.0265   0.0272   1.0000
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