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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 500,000
Max Cl/Cd: 100.92 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkz-il-500000.txt
Download as CSV file: xf-clarkz-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK Z AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3321   0.09602   0.09363  -0.0409   1.0000   0.0346
  -9.250  -0.3347   0.09399   0.09164  -0.0398   1.0000   0.0350
  -9.000  -0.3440   0.09238   0.09009  -0.0375   1.0000   0.0354
  -8.750  -0.3365   0.08894   0.08665  -0.0403   0.9981   0.0363
  -8.500  -0.3426   0.07341   0.07111  -0.0661   0.9870   0.0390
  -8.250  -0.3235   0.07050   0.06820  -0.0681   0.9847   0.0393
  -8.000  -0.2998   0.06730   0.06499  -0.0725   0.9827   0.0397
  -7.750  -0.2798   0.06390   0.06156  -0.0770   0.9767   0.0402
  -7.500  -0.2347   0.03440   0.03167  -0.0965   0.9486   0.0453
  -7.250  -0.2195   0.03192   0.02923  -0.0963   0.9417   0.0458
  -7.000  -0.2051   0.03027   0.02757  -0.0957   0.9319   0.0462
  -6.750  -0.1895   0.02842   0.02565  -0.0955   0.9238   0.0467
  -6.500  -0.1752   0.02629   0.02345  -0.0953   0.9135   0.0475
  -6.250  -0.1605   0.02356   0.02056  -0.0955   0.9046   0.0488
  -6.000  -0.1845   0.02181   0.01668  -0.0984   0.9117   0.0391
  -5.750  -0.1610   0.02050   0.01514  -0.0977   0.9035   0.0390
  -5.500  -0.1375   0.01891   0.01331  -0.0970   0.8953   0.0390
  -5.250  -0.1127   0.01782   0.01203  -0.0964   0.8868   0.0389
  -5.000  -0.0876   0.01665   0.01066  -0.0958   0.8784   0.0389
  -4.750  -0.0625   0.01541   0.00926  -0.0952   0.8694   0.0391
  -4.500  -0.0366   0.01433   0.00803  -0.0947   0.8610   0.0393
  -4.250  -0.0108   0.01349   0.00712  -0.0943   0.8516   0.0397
  -3.750   0.0421   0.01239   0.00592  -0.0934   0.8334   0.0408
  -3.500   0.0690   0.01202   0.00548  -0.0931   0.8246   0.0418
  -3.250   0.0957   0.01166   0.00508  -0.0927   0.8146   0.0427
  -3.000   0.1224   0.01130   0.00466  -0.0923   0.8053   0.0435
  -2.750   0.1493   0.01099   0.00427  -0.0918   0.7957   0.0443
  -2.500   0.1762   0.01074   0.00397  -0.0915   0.7859   0.0450
  -2.250   0.2023   0.01029   0.00348  -0.0910   0.7768   0.0464
  -2.000   0.2290   0.01003   0.00323  -0.0906   0.7667   0.0480
  -1.750   0.2561   0.00986   0.00301  -0.0903   0.7574   0.0500
  -1.500   0.2833   0.00973   0.00284  -0.0900   0.7475   0.0524
  -1.250   0.3101   0.00950   0.00261  -0.0897   0.7379   0.0572
  -1.000   0.3372   0.00934   0.00243  -0.0893   0.7285   0.0647
  -0.750   0.3638   0.00906   0.00231  -0.0890   0.7181   0.1034
  -0.500   0.3903   0.00885   0.00225  -0.0887   0.7084   0.1598
  -0.250   0.4165   0.00860   0.00221  -0.0884   0.6981   0.2355
   0.000   0.4403   0.00796   0.00221  -0.0879   0.6879   0.4495
   0.250   0.4588   0.00714   0.00227  -0.0860   0.6780   0.7404
   0.500   0.4825   0.00681   0.00240  -0.0842   0.6673   0.9238
   0.750   0.5407   0.00688   0.00242  -0.0904   0.6553   0.9890
   1.000   0.5867   0.00697   0.00239  -0.0943   0.6430   1.0000
   1.250   0.6114   0.00706   0.00240  -0.0936   0.6311   1.0000
   1.500   0.6361   0.00715   0.00241  -0.0928   0.6187   1.0000
   1.750   0.6606   0.00726   0.00244  -0.0920   0.6061   1.0000
   2.000   0.6849   0.00738   0.00248  -0.0912   0.5935   1.0000
   2.500   0.7334   0.00764   0.00258  -0.0896   0.5659   1.0000
   2.750   0.7576   0.00778   0.00266  -0.0888   0.5517   1.0000
   3.000   0.7818   0.00793   0.00274  -0.0880   0.5369   1.0000
   3.250   0.8056   0.00811   0.00283  -0.0871   0.5200   1.0000
   3.500   0.8292   0.00832   0.00293  -0.0862   0.5017   1.0000
   3.750   0.8530   0.00852   0.00305  -0.0854   0.4847   1.0000
   4.000   0.8772   0.00873   0.00318  -0.0846   0.4688   1.0000
   4.250   0.9011   0.00896   0.00333  -0.0839   0.4522   1.0000
   4.500   0.9252   0.00919   0.00348  -0.0831   0.4362   1.0000
   4.750   0.9494   0.00943   0.00364  -0.0824   0.4212   1.0000
   5.000   0.9737   0.00966   0.00382  -0.0818   0.4071   1.0000
   5.250   0.9981   0.00989   0.00401  -0.0811   0.3946   1.0000
   5.500   1.0222   0.01015   0.00420  -0.0805   0.3821   1.0000
   5.750   1.0463   0.01040   0.00441  -0.0798   0.3698   1.0000
   6.000   1.0710   0.01062   0.00462  -0.0793   0.3585   1.0000
   6.250   1.0951   0.01088   0.00484  -0.0786   0.3474   1.0000
   6.500   1.1186   0.01117   0.00509  -0.0779   0.3355   1.0000
   6.750   1.1424   0.01144   0.00533  -0.0773   0.3230   1.0000
   7.000   1.1661   0.01172   0.00558  -0.0766   0.3105   1.0000
   7.250   1.1894   0.01201   0.00585  -0.0759   0.2981   1.0000
   7.500   1.2121   0.01234   0.00614  -0.0751   0.2847   1.0000
   7.750   1.2342   0.01270   0.00645  -0.0742   0.2698   1.0000
   8.000   1.2558   0.01309   0.00679  -0.0732   0.2525   1.0000
   8.250   1.2758   0.01357   0.00718  -0.0721   0.2313   1.0000
   8.500   1.2940   0.01416   0.00764  -0.0706   0.2056   1.0000
   8.750   1.3093   0.01492   0.00822  -0.0688   0.1753   1.0000
   9.000   1.3226   0.01574   0.00887  -0.0667   0.1485   1.0000
   9.250   1.3350   0.01653   0.00954  -0.0644   0.1300   1.0000
   9.500   1.3492   0.01722   0.01018  -0.0624   0.1188   1.0000
   9.750   1.3639   0.01789   0.01083  -0.0605   0.1112   1.0000
  10.000   1.3782   0.01859   0.01151  -0.0586   0.1054   1.0000
  10.250   1.3918   0.01933   0.01227  -0.0568   0.1009   1.0000
  10.500   1.4076   0.01995   0.01294  -0.0552   0.0977   1.0000
  10.750   1.4212   0.02072   0.01372  -0.0535   0.0942   1.0000
  11.000   1.4311   0.02172   0.01473  -0.0515   0.0906   1.0000
  11.250   1.4462   0.02244   0.01551  -0.0501   0.0883   1.0000
  11.500   1.4608   0.02319   0.01633  -0.0488   0.0861   1.0000
  11.750   1.4736   0.02409   0.01728  -0.0473   0.0839   1.0000
  12.000   1.4840   0.02517   0.01839  -0.0457   0.0816   1.0000
  12.250   1.4902   0.02659   0.01985  -0.0438   0.0791   1.0000
  12.500   1.5045   0.02748   0.02082  -0.0428   0.0774   1.0000
  12.750   1.5190   0.02835   0.02177  -0.0418   0.0751   1.0000
  13.000   1.5308   0.02945   0.02292  -0.0408   0.0728   1.0000
  13.250   1.5393   0.03085   0.02436  -0.0396   0.0705   1.0000
  13.500   1.5444   0.03259   0.02615  -0.0382   0.0682   1.0000
  13.750   1.5592   0.03354   0.02720  -0.0376   0.0662   1.0000
  14.000   1.5713   0.03472   0.02845  -0.0369   0.0635   1.0000
  14.250   1.5787   0.03637   0.03012  -0.0360   0.0604   1.0000
  14.500   1.5890   0.03779   0.03162  -0.0353   0.0570   1.0000
  14.750   1.5968   0.03947   0.03331  -0.0347   0.0521   1.0000
  15.000   1.6026   0.04137   0.03523  -0.0340   0.0455   1.0000
  15.250   1.6014   0.04404   0.03788  -0.0333   0.0374   1.0000
  15.500   1.5961   0.04726   0.04109  -0.0327   0.0305   1.0000
  15.750   1.5890   0.05080   0.04466  -0.0322   0.0268   1.0000
  16.000   1.5825   0.05442   0.04835  -0.0321   0.0247   1.0000
  16.250   1.5742   0.05839   0.05239  -0.0321   0.0233   1.0000
  16.500   1.5683   0.06217   0.05630  -0.0324   0.0224   1.0000
  16.750   1.5607   0.06628   0.06051  -0.0328   0.0216   1.0000
  17.000   1.5513   0.07076   0.06509  -0.0335   0.0210   1.0000
  17.250   1.5399   0.07561   0.07004  -0.0344   0.0205   1.0000
  17.500   1.5261   0.08091   0.07545  -0.0356   0.0200   1.0000
  17.750   1.5128   0.08628   0.08094  -0.0370   0.0197   1.0000
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