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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.63 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkz-il-1000000.txt
Download as CSV file: xf-clarkz-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3198   0.08356   0.08187  -0.0505   0.9950   0.0269
  -8.750  -0.2348   0.05872   0.05707  -0.0692   0.9703   0.0292
  -8.500  -0.4010   0.03362   0.03097  -0.0990   0.9520   0.0290
  -8.250  -0.3843   0.03192   0.02920  -0.0987   0.9431   0.0293
  -8.000  -0.3775   0.02693   0.02383  -0.0983   0.9323   0.0275
  -7.750  -0.3690   0.02210   0.01839  -0.0975   0.9225   0.0274
  -7.500  -0.3509   0.01967   0.01561  -0.0967   0.9134   0.0274
  -7.250  -0.3293   0.01803   0.01369  -0.0961   0.9054   0.0276
  -7.000  -0.3061   0.01679   0.01222  -0.0955   0.8969   0.0278
  -6.750  -0.2815   0.01583   0.01108  -0.0950   0.8889   0.0280
  -6.500  -0.2563   0.01508   0.01016  -0.0945   0.8802   0.0282
  -6.250  -0.2303   0.01451   0.00945  -0.0941   0.8719   0.0284
  -6.000  -0.2047   0.01379   0.00856  -0.0937   0.8628   0.0288
  -5.750  -0.1800   0.01261   0.00726  -0.0933   0.8538   0.0293
  -5.500  -0.1540   0.01203   0.00659  -0.0929   0.8444   0.0295
  -5.250  -0.1274   0.01157   0.00609  -0.0926   0.8351   0.0299
  -5.000  -0.1008   0.01118   0.00563  -0.0923   0.8259   0.0302
  -4.750  -0.0738   0.01082   0.00522  -0.0920   0.8163   0.0305
  -4.500  -0.0469   0.01049   0.00482  -0.0917   0.8071   0.0309
  -4.250  -0.0200   0.01018   0.00446  -0.0914   0.7972   0.0313
  -4.000   0.0071   0.00989   0.00411  -0.0911   0.7876   0.0317
  -3.500   0.0613   0.00941   0.00352  -0.0906   0.7679   0.0326
  -3.250   0.0886   0.00923   0.00328  -0.0903   0.7584   0.0331
  -3.000   0.1158   0.00900   0.00301  -0.0901   0.7485   0.0337
  -2.750   0.1425   0.00867   0.00264  -0.0898   0.7394   0.0346
  -2.500   0.1698   0.00851   0.00244  -0.0895   0.7297   0.0354
  -2.250   0.1974   0.00837   0.00228  -0.0894   0.7202   0.0363
  -2.000   0.2248   0.00828   0.00213  -0.0891   0.7108   0.0373
  -1.750   0.2527   0.00817   0.00200  -0.0890   0.7012   0.0383
  -1.500   0.2801   0.00806   0.00184  -0.0888   0.6917   0.0397
  -1.250   0.3076   0.00795   0.00172  -0.0886   0.6817   0.0421
  -1.000   0.3354   0.00788   0.00163  -0.0884   0.6721   0.0447
  -0.750   0.3626   0.00780   0.00154  -0.0882   0.6617   0.0516
  -0.500   0.3898   0.00760   0.00148  -0.0880   0.6516   0.0894
  -0.250   0.4170   0.00749   0.00146  -0.0878   0.6416   0.1282
   0.000   0.4441   0.00741   0.00144  -0.0876   0.6305   0.1648
   0.500   0.4968   0.00691   0.00146  -0.0872   0.6090   0.3697
   0.750   0.5204   0.00637   0.00150  -0.0866   0.5974   0.5984
   1.000   0.5413   0.00584   0.00159  -0.0851   0.5857   0.8121
   1.250   0.5649   0.00566   0.00171  -0.0835   0.5740   0.9474
   1.500   0.6112   0.00579   0.00177  -0.0874   0.5597   0.9876
   1.750   0.6600   0.00593   0.00182  -0.0920   0.5437   0.9985
   2.000   0.6901   0.00606   0.00186  -0.0925   0.5291   1.0000
   2.250   0.7143   0.00619   0.00191  -0.0917   0.5139   1.0000
   2.500   0.7384   0.00635   0.00198  -0.0909   0.4960   1.0000
   2.750   0.7623   0.00652   0.00205  -0.0900   0.4765   1.0000
   3.000   0.7863   0.00669   0.00213  -0.0892   0.4602   1.0000
   3.250   0.8104   0.00686   0.00223  -0.0884   0.4448   1.0000
   3.500   0.8345   0.00704   0.00233  -0.0876   0.4288   1.0000
   3.750   0.8587   0.00723   0.00243  -0.0869   0.4131   1.0000
   4.000   0.8832   0.00742   0.00255  -0.0862   0.3992   1.0000
   4.500   0.9328   0.00781   0.00280  -0.0850   0.3713   1.0000
   4.750   0.9581   0.00799   0.00294  -0.0845   0.3594   1.0000
   5.000   0.9833   0.00818   0.00308  -0.0840   0.3486   1.0000
   5.500   1.0338   0.00857   0.00338  -0.0830   0.3269   1.0000
   5.750   1.0588   0.00878   0.00355  -0.0825   0.3155   1.0000
   6.000   1.0836   0.00902   0.00373  -0.0820   0.3036   1.0000
   6.250   1.1085   0.00924   0.00391  -0.0815   0.2920   1.0000
   6.500   1.1334   0.00947   0.00410  -0.0810   0.2803   1.0000
   6.750   1.1578   0.00973   0.00431  -0.0805   0.2675   1.0000
   7.000   1.1818   0.01002   0.00454  -0.0799   0.2531   1.0000
   7.250   1.2051   0.01035   0.00480  -0.0792   0.2360   1.0000
   7.500   1.2270   0.01078   0.00510  -0.0783   0.2149   1.0000
   7.750   1.2480   0.01127   0.00546  -0.0773   0.1903   1.0000
   8.000   1.2672   0.01188   0.00590  -0.0760   0.1621   1.0000
   8.250   1.2856   0.01252   0.00639  -0.0745   0.1361   1.0000
   8.500   1.3041   0.01314   0.00687  -0.0732   0.1163   1.0000
   8.750   1.3239   0.01364   0.00730  -0.0720   0.1047   1.0000
   9.000   1.3446   0.01407   0.00771  -0.0709   0.0977   1.0000
   9.250   1.3640   0.01455   0.00815  -0.0697   0.0912   1.0000
   9.500   1.3842   0.01491   0.00853  -0.0685   0.0880   1.0000
   9.750   1.4030   0.01531   0.00893  -0.0671   0.0849   1.0000
  10.000   1.4204   0.01578   0.00940  -0.0656   0.0815   1.0000
  10.250   1.4374   0.01627   0.00991  -0.0640   0.0784   1.0000
  10.500   1.4569   0.01663   0.01030  -0.0628   0.0769   1.0000
  10.750   1.4751   0.01707   0.01076  -0.0615   0.0746   1.0000
  11.000   1.4917   0.01759   0.01130  -0.0600   0.0722   1.0000
  11.250   1.5070   0.01821   0.01193  -0.0584   0.0696   1.0000
  11.500   1.5235   0.01876   0.01251  -0.0570   0.0678   1.0000
  11.750   1.5413   0.01923   0.01304  -0.0559   0.0664   1.0000
  12.000   1.5577   0.01980   0.01364  -0.0546   0.0644   1.0000
  12.250   1.5720   0.02051   0.01434  -0.0531   0.0615   1.0000
  12.500   1.5860   0.02127   0.01513  -0.0516   0.0587   1.0000
  12.750   1.6019   0.02191   0.01581  -0.0505   0.0564   1.0000
  13.000   1.6144   0.02280   0.01668  -0.0490   0.0527   1.0000
  13.250   1.6270   0.02370   0.01761  -0.0477   0.0489   1.0000
  13.500   1.6359   0.02489   0.01877  -0.0461   0.0428   1.0000
  13.750   1.6379   0.02666   0.02046  -0.0440   0.0317   1.0000
  14.000   1.6334   0.02901   0.02276  -0.0417   0.0222   1.0000
  14.250   1.6345   0.03104   0.02483  -0.0400   0.0192   1.0000
  14.500   1.6374   0.03299   0.02683  -0.0386   0.0179   1.0000
  14.750   1.6381   0.03521   0.02910  -0.0373   0.0167   1.0000
  15.000   1.6422   0.03719   0.03117  -0.0363   0.0161   1.0000
  15.250   1.6448   0.03936   0.03342  -0.0354   0.0156   1.0000
  15.500   1.6455   0.04180   0.03594  -0.0346   0.0150   1.0000
  15.750   1.6444   0.04452   0.03874  -0.0340   0.0146   1.0000
  16.000   1.6409   0.04761   0.04191  -0.0335   0.0141   1.0000
  16.250   1.6353   0.05104   0.04544  -0.0332   0.0138   1.0000
  16.500   1.6351   0.05395   0.04845  -0.0331   0.0136   1.0000
  16.750   1.6332   0.05714   0.05173  -0.0331   0.0133   1.0000
  17.000   1.6296   0.06060   0.05529  -0.0333   0.0131   1.0000
  17.250   1.6244   0.06434   0.05913  -0.0336   0.0129   1.0000
  17.500   1.6180   0.06835   0.06324  -0.0342   0.0127   1.0000
  17.750   1.6104   0.07260   0.06759  -0.0349   0.0125   1.0000
  18.000   1.6014   0.07709   0.07219  -0.0358   0.0123   1.0000
  18.250   1.5906   0.08195   0.07716  -0.0369   0.0122   1.0000
  18.500   1.5785   0.08710   0.08242  -0.0382   0.0120   1.0000
  18.750   1.5651   0.09250   0.08793  -0.0397   0.0119   1.0000
  19.000   1.5496   0.09830   0.09384  -0.0414   0.0118   1.0000
  19.250   1.5335   0.10431   0.09996  -0.0434   0.0117   1.0000
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