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CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 100,000
Max Cl/Cd: 57.62 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkv-il-100000.txt
Download as CSV file: xf-clarkv-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK V AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4133   0.10727   0.10230  -0.0359   1.0000   0.1235
  -9.000  -0.4513   0.10618   0.10138  -0.0370   1.0000   0.1252
  -8.750  -0.4867   0.10483   0.10017  -0.0364   1.0000   0.1255
  -8.500  -0.4308   0.09894   0.09416  -0.0321   1.0000   0.1304
  -8.250  -0.4359   0.09678   0.09205  -0.0302   1.0000   0.1339
  -8.000  -0.4562   0.09491   0.09028  -0.0286   1.0000   0.1372
  -7.750  -0.4932   0.09338   0.08890  -0.0275   1.0000   0.1391
  -7.250  -0.5171   0.08654   0.08217  -0.0266   1.0000   0.1434
  -7.000  -0.5104   0.08469   0.08034  -0.0230   1.0000   0.1479
  -6.750  -0.5549   0.07987   0.07528  -0.0331   1.0000   0.1564
  -6.500  -0.5349   0.07700   0.07265  -0.0261   1.0000   0.1590
  -6.250  -0.5276   0.07528   0.07095  -0.0228   1.0000   0.1647
  -6.000  -0.5350   0.07064   0.06620  -0.0262   1.0000   0.1743
  -5.750  -0.5265   0.06862   0.06423  -0.0234   1.0000   0.1792
  -5.500  -0.5238   0.06474   0.06022  -0.0253   1.0000   0.1908
  -5.250  -0.4982   0.04557   0.03936  -0.0389   1.0000   0.1130
  -5.000  -0.4853   0.04648   0.04063  -0.0370   1.0000   0.1307
  -4.750  -0.4509   0.03694   0.02915  -0.0395   1.0000   0.0963
  -4.500  -0.4283   0.03428   0.02617  -0.0395   1.0000   0.0955
  -4.250  -0.4050   0.03259   0.02402  -0.0392   1.0000   0.0963
  -4.000  -0.3817   0.03055   0.02175  -0.0392   1.0000   0.0984
  -3.750  -0.3583   0.02925   0.02024  -0.0389   1.0000   0.1000
  -3.500  -0.3254   0.02816   0.01896  -0.0403   0.9977   0.1023
  -3.250  -0.2821   0.02739   0.01795  -0.0435   0.9930   0.1073
  -3.000  -0.2418   0.02656   0.01697  -0.0461   0.9875   0.1136
  -2.750  -0.1986   0.02605   0.01644  -0.0493   0.9831   0.1220
  -2.500  -0.1631   0.02539   0.01586  -0.0512   0.9765   0.1338
  -2.250  -0.1201   0.02485   0.01546  -0.0544   0.9719   0.1602
  -2.000  -0.0862   0.02398   0.01502  -0.0562   0.9655   0.2206
  -1.750  -0.0493   0.02254   0.01516  -0.0585   0.9612   0.5217
  -1.500  -0.0204   0.02189   0.01577  -0.0564   0.9574   0.8741
  -1.250   0.0180   0.02198   0.01566  -0.0591   0.9472   1.0000
  -1.000   0.0562   0.02238   0.01576  -0.0617   0.9401   1.0000
  -0.750   0.0910   0.02270   0.01586  -0.0636   0.9319   1.0000
  -0.500   0.1247   0.02303   0.01601  -0.0652   0.9238   1.0000
  -0.250   0.1627   0.02333   0.01613  -0.0676   0.9163   1.0000
   0.000   0.1924   0.02363   0.01630  -0.0684   0.9071   1.0000
   0.250   0.2343   0.02387   0.01640  -0.0713   0.9007   1.0000
   0.500   0.2611   0.02413   0.01657  -0.0715   0.8903   1.0000
   0.750   0.3077   0.02422   0.01656  -0.0751   0.8849   1.0000
   1.000   0.3334   0.02440   0.01667  -0.0749   0.8732   1.0000
   1.250   0.3659   0.02448   0.01670  -0.0758   0.8631   1.0000
   1.500   0.4118   0.02426   0.01643  -0.0788   0.8563   1.0000
   1.750   0.4393   0.02434   0.01648  -0.0787   0.8448   1.0000
   2.000   0.4891   0.02392   0.01604  -0.0821   0.8402   1.0000
   2.250   0.5132   0.02402   0.01615  -0.0814   0.8280   1.0000
   2.500   0.5436   0.02398   0.01611  -0.0816   0.8178   1.0000
   2.750   0.5898   0.02337   0.01553  -0.0842   0.8121   1.0000
   3.000   0.6186   0.02324   0.01543  -0.0839   0.8011   1.0000
   3.250   0.6696   0.02229   0.01454  -0.0870   0.7962   1.0000
   3.500   0.6995   0.02197   0.01427  -0.0866   0.7842   1.0000
   3.750   0.7389   0.02120   0.01354  -0.0876   0.7739   1.0000
   4.000   0.7875   0.02006   0.01248  -0.0898   0.7651   1.0000
   4.250   0.8196   0.01959   0.01206  -0.0897   0.7511   1.0000
   4.500   0.8523   0.01916   0.01168  -0.0897   0.7367   1.0000
   4.750   0.8856   0.01874   0.01132  -0.0897   0.7212   1.0000
   5.000   0.9191   0.01835   0.01096  -0.0899   0.7043   1.0000
   5.250   0.9458   0.01820   0.01084  -0.0889   0.6839   1.0000
   5.500   0.9731   0.01807   0.01074  -0.0880   0.6615   1.0000
   5.750   0.9993   0.01802   0.01067  -0.0870   0.6369   1.0000
   6.000   1.0246   0.01803   0.01062  -0.0858   0.6091   1.0000
   6.250   1.0454   0.01819   0.01071  -0.0838   0.5774   1.0000
   6.500   1.0637   0.01846   0.01091  -0.0815   0.5431   1.0000
   6.750   1.0812   0.01884   0.01117  -0.0792   0.5085   1.0000
   7.000   1.0982   0.01934   0.01152  -0.0769   0.4747   1.0000
   7.250   1.1144   0.01996   0.01197  -0.0746   0.4422   1.0000
   7.500   1.1298   0.02066   0.01253  -0.0722   0.4111   1.0000
   7.750   1.1448   0.02144   0.01319  -0.0699   0.3819   1.0000
   8.000   1.1596   0.02227   0.01393  -0.0677   0.3547   1.0000
   8.250   1.1752   0.02317   0.01471  -0.0656   0.3301   1.0000
   8.500   1.1895   0.02406   0.01553  -0.0634   0.3068   1.0000
   8.750   1.2006   0.02491   0.01634  -0.0607   0.2837   1.0000
   9.000   1.2080   0.02568   0.01706  -0.0575   0.2614   1.0000
   9.250   1.2130   0.02646   0.01781  -0.0539   0.2404   1.0000
   9.500   1.2180   0.02732   0.01867  -0.0504   0.2199   1.0000
   9.750   1.2238   0.02833   0.01965  -0.0473   0.2011   1.0000
  10.000   1.2289   0.02947   0.02078  -0.0442   0.1818   1.0000
  10.250   1.2319   0.03074   0.02206  -0.0411   0.1614   1.0000
  10.500   1.2322   0.03231   0.02352  -0.0378   0.1410   1.0000
  10.750   1.2305   0.03409   0.02529  -0.0345   0.1180   1.0000
  11.000   1.2287   0.03627   0.02731  -0.0314   0.0997   1.0000
  11.250   1.2313   0.03848   0.02945  -0.0287   0.0866   1.0000
  11.500   1.2373   0.04060   0.03144  -0.0267   0.0774   1.0000
  11.750   1.2462   0.04253   0.03357  -0.0247   0.0705   1.0000
  12.000   1.2642   0.04473   0.03560  -0.0237   0.0651   1.0000
  12.250   1.2764   0.04679   0.03795  -0.0221   0.0616   1.0000
  12.500   1.2874   0.04880   0.04007  -0.0206   0.0582   1.0000
  12.750   1.3097   0.05143   0.04262  -0.0203   0.0547   1.0000
  13.000   1.3133   0.05398   0.04555  -0.0183   0.0532   1.0000
  13.250   1.3169   0.05691   0.04880  -0.0165   0.0520   1.0000
  13.500   1.3166   0.06008   0.05228  -0.0146   0.0511   1.0000
  13.750   1.3121   0.06348   0.05597  -0.0128   0.0504   1.0000
  14.000   1.3037   0.06708   0.05985  -0.0112   0.0499   1.0000
  14.250   1.2926   0.07090   0.06394  -0.0099   0.0494   1.0000
  14.500   1.2784   0.07507   0.06837  -0.0090   0.0490   1.0000
  14.750   1.2601   0.07978   0.07335  -0.0086   0.0488   1.0000
  15.000   1.2349   0.08545   0.07932  -0.0092   0.0490   1.0000
  15.250   1.2009   0.09274   0.08694  -0.0112   0.0497   1.0000
  15.500   1.1644   0.10131   0.09582  -0.0148   0.0507   1.0000
  15.750   1.1273   0.11119   0.10595  -0.0202   0.0518   1.0000
  16.000   1.0903   0.12244   0.11737  -0.0272   0.0530   1.0000
  16.250   1.0565   0.13454   0.12958  -0.0348   0.0541   1.0000
  16.500   1.0334   0.14533   0.14040  -0.0409   0.0550   1.0000
  16.750   0.9473   0.18729   0.18221  -0.0645   0.0765   1.0000
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