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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 50,000
Max Cl/Cd: 36.46 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkw-il-50000-n5.txt
Download as CSV file: xf-clarkw-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK W AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3760   0.10213   0.09454  -0.0404   1.0000   0.0826
  -9.000  -0.3812   0.09879   0.09128  -0.0406   1.0000   0.0810
  -8.750  -0.3908   0.09532   0.08792  -0.0408   1.0000   0.0794
  -8.250  -0.4490   0.08618   0.07907  -0.0432   1.0000   0.0750
  -8.000  -0.4563   0.08320   0.07615  -0.0422   1.0000   0.0747
  -7.750  -0.4647   0.08000   0.07300  -0.0415   1.0000   0.0743
  -7.500  -0.4733   0.07651   0.06953  -0.0411   1.0000   0.0739
  -7.250  -0.4811   0.07265   0.06566  -0.0409   1.0000   0.0735
  -7.000  -0.4880   0.06826   0.06120  -0.0412   1.0000   0.0732
  -6.750  -0.4937   0.06328   0.05607  -0.0418   1.0000   0.0733
  -6.500  -0.4967   0.05806   0.05057  -0.0426   1.0000   0.0738
  -6.250  -0.4951   0.05300   0.04509  -0.0433   1.0000   0.0744
  -6.000  -0.4882   0.04849   0.04006  -0.0435   1.0000   0.0751
  -5.750  -0.4761   0.04540   0.03666  -0.0431   1.0000   0.0757
  -5.500  -0.4614   0.04289   0.03387  -0.0426   1.0000   0.0763
  -5.250  -0.4335   0.04033   0.03096  -0.0444   0.9962   0.0775
  -5.000  -0.4021   0.03800   0.02825  -0.0465   0.9914   0.0791
  -4.750  -0.3697   0.03607   0.02593  -0.0485   0.9864   0.0819
  -4.500  -0.3363   0.03420   0.02354  -0.0504   0.9817   0.0859
  -4.250  -0.3037   0.03275   0.02181  -0.0519   0.9763   0.0894
  -4.000  -0.2688   0.03164   0.02053  -0.0538   0.9716   0.0933
  -3.750  -0.2371   0.03052   0.01914  -0.0548   0.9655   0.0983
  -3.500  -0.2012   0.02960   0.01812  -0.0567   0.9605   0.1057
  -3.250  -0.1694   0.02887   0.01724  -0.0578   0.9541   0.1177
  -3.000  -0.1342   0.02820   0.01657  -0.0595   0.9482   0.1348
  -2.750  -0.0993   0.02769   0.01604  -0.0610   0.9421   0.1608
  -2.500  -0.0674   0.02746   0.01593  -0.0623   0.9344   0.1959
  -2.250  -0.0324   0.02746   0.01606  -0.0641   0.9276   0.2407
  -2.000  -0.0021   0.02729   0.01593  -0.0647   0.9188   0.2742
  -1.750   0.0352   0.02708   0.01570  -0.0665   0.9120   0.3103
  -1.500   0.0655   0.02688   0.01551  -0.0670   0.9024   0.3436
  -1.250   0.1000   0.02660   0.01526  -0.0683   0.8942   0.3801
  -1.000   0.1330   0.02624   0.01500  -0.0693   0.8852   0.4192
  -0.750   0.1635   0.02581   0.01475  -0.0697   0.8758   0.4633
  -0.500   0.1970   0.02502   0.01444  -0.0706   0.8680   0.5402
  -0.250   0.2569   0.02404   0.01441  -0.0755   0.8610   1.0000
   0.000   0.2942   0.02404   0.01414  -0.0770   0.8519   1.0000
   0.250   0.3213   0.02415   0.01406  -0.0768   0.8400   1.0000
   0.500   0.3546   0.02415   0.01387  -0.0774   0.8301   1.0000
   0.750   0.3875   0.02412   0.01369  -0.0780   0.8199   1.0000
   1.000   0.4135   0.02420   0.01366  -0.0774   0.8072   1.0000
   1.250   0.4431   0.02420   0.01356  -0.0773   0.7958   1.0000
   1.500   0.4782   0.02404   0.01330  -0.0780   0.7861   1.0000
   2.000   0.5288   0.02417   0.01331  -0.0763   0.7590   1.0000
   2.250   0.5568   0.02415   0.01325  -0.0758   0.7462   1.0000
   2.500   0.5877   0.02403   0.01309  -0.0757   0.7342   1.0000
   2.750   0.6167   0.02396   0.01298  -0.0752   0.7210   1.0000
   3.000   0.6419   0.02402   0.01303  -0.0743   0.7060   1.0000
   3.250   0.6675   0.02407   0.01306  -0.0734   0.6909   1.0000
   3.500   0.6934   0.02413   0.01310  -0.0725   0.6757   1.0000
   3.750   0.7195   0.02420   0.01317  -0.0717   0.6602   1.0000
   4.000   0.7455   0.02429   0.01325  -0.0709   0.6446   1.0000
   4.250   0.7713   0.02442   0.01337  -0.0700   0.6287   1.0000
   4.500   0.7969   0.02458   0.01354  -0.0692   0.6130   1.0000
   4.750   0.8223   0.02479   0.01374  -0.0684   0.5972   1.0000
   5.000   0.8473   0.02504   0.01399  -0.0675   0.5816   1.0000
   5.250   0.8721   0.02534   0.01431  -0.0667   0.5663   1.0000
   5.500   0.8967   0.02567   0.01465  -0.0658   0.5513   1.0000
   5.750   0.9214   0.02604   0.01503  -0.0650   0.5371   1.0000
   6.000   0.9463   0.02642   0.01545  -0.0643   0.5231   1.0000
   6.250   0.9720   0.02681   0.01584  -0.0636   0.5098   1.0000
   6.500   0.9940   0.02736   0.01647  -0.0626   0.4959   1.0000
   6.750   1.0157   0.02794   0.01714  -0.0615   0.4821   1.0000
   7.000   1.0373   0.02850   0.01776  -0.0604   0.4680   1.0000
   7.250   1.0578   0.02901   0.01831  -0.0590   0.4523   1.0000
   7.750   1.0954   0.03010   0.01950  -0.0557   0.4198   1.0000
   8.000   1.1136   0.03072   0.02019  -0.0541   0.4046   1.0000
   8.250   1.1313   0.03138   0.02093  -0.0525   0.3898   1.0000
   8.500   1.1474   0.03206   0.02172  -0.0506   0.3745   1.0000
   8.750   1.1607   0.03275   0.02250  -0.0484   0.3578   1.0000
   9.000   1.1709   0.03348   0.02330  -0.0458   0.3399   1.0000
   9.250   1.1785   0.03425   0.02412  -0.0429   0.3211   1.0000
   9.500   1.1833   0.03506   0.02496  -0.0397   0.3025   1.0000
   9.750   1.1863   0.03602   0.02592  -0.0364   0.2840   1.0000
  10.000   1.1872   0.03726   0.02729  -0.0333   0.2642   1.0000
  10.250   1.1882   0.03864   0.02872  -0.0305   0.2442   1.0000
  10.500   1.1884   0.04019   0.03026  -0.0279   0.2245   1.0000
  10.750   1.1878   0.04201   0.03205  -0.0256   0.2052   1.0000
  11.000   1.1866   0.04408   0.03414  -0.0235   0.1864   1.0000
  11.250   1.1848   0.04637   0.03640  -0.0217   0.1701   1.0000
  11.500   1.1824   0.04887   0.03886  -0.0202   0.1562   1.0000
  11.750   1.1799   0.05154   0.04151  -0.0188   0.1446   1.0000
  12.000   1.1772   0.05430   0.04417  -0.0176   0.1353   1.0000
  12.250   1.1764   0.05713   0.04709  -0.0166   0.1259   1.0000
  12.500   1.1755   0.05997   0.04994  -0.0157   0.1186   1.0000
  12.750   1.1753   0.06286   0.05290  -0.0150   0.1115   1.0000
  13.000   1.1767   0.06561   0.05566  -0.0142   0.1059   1.0000
  13.250   1.1771   0.06868   0.05892  -0.0138   0.1003   1.0000
  13.500   1.1797   0.07130   0.06151  -0.0132   0.0956   1.0000
  13.750   1.1788   0.07470   0.06515  -0.0130   0.0914   1.0000
  14.000   1.1770   0.07824   0.06890  -0.0130   0.0876   1.0000
  14.250   1.1788   0.08114   0.07185  -0.0128   0.0840   1.0000
  14.500   1.1786   0.08454   0.07535  -0.0129   0.0810   1.0000
  14.750   1.1684   0.08961   0.08074  -0.0141   0.0786   1.0000
  15.000   1.1587   0.09475   0.08612  -0.0155   0.0765   1.0000
  15.250   1.1502   0.09979   0.09133  -0.0171   0.0746   1.0000
  15.500   1.1489   0.10352   0.09513  -0.0179   0.0723   1.0000
  15.750   1.1442   0.10803   0.09971  -0.0193   0.0705   1.0000
  16.000   1.1188   0.11694   0.10892  -0.0239   0.0700   1.0000
  16.250   1.0874   0.12793   0.12017  -0.0302   0.0699   1.0000
  16.500   1.0465   0.14257   0.13501  -0.0390   0.0702   1.0000
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