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


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 100,000
Max Cl/Cd: 54.2 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkx-il-100000.txt
Download as CSV file: xf-clarkx-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3797   0.11686   0.11149  -0.0338   1.0000   0.1179
 -10.250  -0.3719   0.11391   0.10854  -0.0338   1.0000   0.1220
 -10.000  -0.3796   0.11142   0.10611  -0.0363   1.0000   0.1270
  -9.750  -0.4196   0.11040   0.10529  -0.0428   1.0000   0.1289
  -9.500  -0.3815   0.10430   0.09910  -0.0381   1.0000   0.1315
  -9.250  -0.3678   0.10151   0.09631  -0.0365   1.0000   0.1357
  -9.000  -0.3750   0.09913   0.09400  -0.0375   1.0000   0.1415
  -8.750  -0.4174   0.09803   0.09311  -0.0400   1.0000   0.1439
  -8.500  -0.3927   0.09332   0.08837  -0.0372   1.0000   0.1473
  -8.250  -0.3838   0.09098   0.08605  -0.0351   1.0000   0.1514
  -8.000  -0.3971   0.08914   0.08430  -0.0334   1.0000   0.1553
  -7.750  -0.4337   0.08827   0.08361  -0.0305   1.0000   0.1579
  -7.500  -0.4942   0.08664   0.08211  -0.0336   1.0000   0.1598
  -7.250  -0.4858   0.08303   0.07857  -0.0294   1.0000   0.1618
  -7.000  -0.4754   0.08115   0.07672  -0.0248   1.0000   0.1645
  -6.750  -0.4805   0.07917   0.07478  -0.0226   1.0000   0.1683
  -6.500  -0.5158   0.07493   0.07046  -0.0285   1.0000   0.1768
  -6.250  -0.5066   0.07277   0.06839  -0.0241   1.0000   0.1789
  -6.000  -0.5020   0.07106   0.06671  -0.0212   1.0000   0.1837
  -5.750  -0.5080   0.06731   0.06287  -0.0236   1.0000   0.1941
  -5.500  -0.5008   0.06566   0.06125  -0.0208   1.0000   0.1997
  -5.250  -0.4788   0.04106   0.03446  -0.0402   0.9994   0.1121
  -5.000  -0.4415   0.03714   0.02998  -0.0440   0.9950   0.1116
  -4.750  -0.4036   0.03413   0.02636  -0.0471   0.9901   0.1124
  -4.500  -0.3635   0.03172   0.02337  -0.0501   0.9851   0.1131
  -4.250  -0.3257   0.02966   0.02100  -0.0529   0.9802   0.1164
  -4.000  -0.2880   0.02857   0.01981  -0.0554   0.9741   0.1214
  -3.750  -0.2454   0.02741   0.01827  -0.0584   0.9693   0.1261
  -3.500  -0.2112   0.02630   0.01699  -0.0600   0.9622   0.1317
  -3.250  -0.1683   0.02560   0.01620  -0.0631   0.9570   0.1411
  -3.000  -0.1358   0.02476   0.01533  -0.0643   0.9495   0.1490
  -2.750  -0.0950   0.02410   0.01466  -0.0670   0.9436   0.1630
  -2.500  -0.0603   0.02350   0.01414  -0.0686   0.9366   0.1788
  -2.250  -0.0233   0.02293   0.01375  -0.0706   0.9295   0.2046
  -2.000   0.0152   0.02235   0.01348  -0.0728   0.9235   0.2529
  -1.750   0.0465   0.02151   0.01329  -0.0738   0.9154   0.3634
  -1.500   0.0853   0.02036   0.01321  -0.0757   0.9109   0.5817
  -1.250   0.1177   0.01972   0.01355  -0.0742   0.9037   0.9396
  -1.000   0.1745   0.01971   0.01325  -0.0800   0.8977   1.0000
  -0.750   0.2067   0.01985   0.01319  -0.0810   0.8883   1.0000
  -0.500   0.2514   0.01981   0.01296  -0.0842   0.8817   1.0000
  -0.250   0.2810   0.01994   0.01295  -0.0846   0.8715   1.0000
   0.000   0.3266   0.01975   0.01261  -0.0876   0.8655   1.0000
   0.250   0.3528   0.01987   0.01264  -0.0872   0.8544   1.0000
   0.500   0.3980   0.01953   0.01220  -0.0898   0.8489   1.0000
   1.000   0.4575   0.01946   0.01199  -0.0898   0.8293   1.0000
   1.250   0.4883   0.01935   0.01183  -0.0898   0.8196   1.0000
   1.500   0.5149   0.01938   0.01181  -0.0892   0.8089   1.0000
   1.750   0.5529   0.01899   0.01138  -0.0902   0.8020   1.0000
   2.000   0.5764   0.01908   0.01144  -0.0891   0.7897   1.0000
   2.250   0.6046   0.01901   0.01135  -0.0885   0.7792   1.0000
   2.500   0.6394   0.01864   0.01095  -0.0888   0.7707   1.0000
   2.750   0.6636   0.01868   0.01098  -0.0877   0.7577   1.0000
   3.000   0.6901   0.01864   0.01093  -0.0869   0.7453   1.0000
   3.250   0.7191   0.01846   0.01074  -0.0863   0.7334   1.0000
   3.500   0.7506   0.01816   0.01039  -0.0860   0.7217   1.0000
   3.750   0.7779   0.01803   0.01023  -0.0851   0.7075   1.0000
   4.000   0.8037   0.01798   0.01018  -0.0841   0.6924   1.0000
   4.250   0.8295   0.01796   0.01015  -0.0831   0.6771   1.0000
   4.500   0.8554   0.01797   0.01015  -0.0822   0.6615   1.0000
   4.750   0.8813   0.01799   0.01016  -0.0812   0.6455   1.0000
   5.000   0.9073   0.01803   0.01018  -0.0804   0.6290   1.0000
   5.250   0.9308   0.01819   0.01034  -0.0791   0.6107   1.0000
   5.500   0.9542   0.01837   0.01054  -0.0780   0.5920   1.0000
   5.750   0.9783   0.01854   0.01071  -0.0769   0.5728   1.0000
   6.000   1.0030   0.01873   0.01085  -0.0758   0.5534   1.0000
   6.250   1.0268   0.01901   0.01108  -0.0748   0.5336   1.0000
   6.500   1.0484   0.01939   0.01148  -0.0734   0.5126   1.0000
   6.750   1.0715   0.01977   0.01183  -0.0723   0.4923   1.0000
   7.000   1.0949   0.02021   0.01218  -0.0712   0.4725   1.0000
   7.250   1.1151   0.02075   0.01277  -0.0698   0.4517   1.0000
   7.500   1.1362   0.02127   0.01326  -0.0685   0.4313   1.0000
   7.750   1.1556   0.02171   0.01361  -0.0668   0.4094   1.0000
   8.000   1.1709   0.02212   0.01402  -0.0646   0.3850   1.0000
   8.250   1.1862   0.02258   0.01441  -0.0624   0.3620   1.0000
   8.500   1.2000   0.02308   0.01493  -0.0601   0.3396   1.0000
   8.750   1.2142   0.02365   0.01544  -0.0579   0.3193   1.0000
   9.000   1.2272   0.02425   0.01612  -0.0556   0.2997   1.0000
   9.250   1.2382   0.02486   0.01681  -0.0531   0.2792   1.0000
   9.500   1.2459   0.02556   0.01751  -0.0501   0.2573   1.0000
   9.750   1.2474   0.02636   0.01836  -0.0463   0.2292   1.0000
  10.000   1.2414   0.02772   0.01960  -0.0418   0.1860   1.0000
  10.250   1.2273   0.03023   0.02165  -0.0372   0.1285   1.0000
  10.500   1.2184   0.03284   0.02393  -0.0336   0.1013   1.0000
  10.750   1.2136   0.03530   0.02624  -0.0307   0.0894   1.0000
  11.000   1.2134   0.03750   0.02848  -0.0284   0.0811   1.0000
  11.250   1.2133   0.03983   0.03079  -0.0262   0.0756   1.0000
  11.500   1.2176   0.04188   0.03291  -0.0243   0.0710   1.0000
  11.750   1.2239   0.04404   0.03494  -0.0224   0.0674   1.0000
  12.000   1.2359   0.04584   0.03688  -0.0209   0.0641   1.0000
  12.250   1.2474   0.04769   0.03879  -0.0195   0.0608   1.0000
  12.500   1.2672   0.04948   0.04044  -0.0184   0.0575   1.0000
  12.750   1.2916   0.05163   0.04271  -0.0174   0.0556   1.0000
  13.000   1.3056   0.05397   0.04533  -0.0162   0.0543   1.0000
  13.250   1.3151   0.05655   0.04815  -0.0150   0.0530   1.0000
  13.500   1.3215   0.05921   0.05102  -0.0137   0.0516   1.0000
  13.750   1.3264   0.06194   0.05392  -0.0126   0.0503   1.0000
  14.000   1.3296   0.06495   0.05709  -0.0116   0.0493   1.0000
  14.250   1.3306   0.06841   0.06074  -0.0107   0.0487   1.0000
  14.500   1.3245   0.07227   0.06485  -0.0098   0.0485   1.0000
  14.750   1.3125   0.07645   0.06932  -0.0091   0.0485   1.0000
  15.000   1.2953   0.08106   0.07422  -0.0090   0.0487   1.0000
  15.250   1.2728   0.08633   0.07980  -0.0097   0.0490   1.0000
  15.500   1.2430   0.09269   0.08650  -0.0115   0.0495   1.0000
  15.750   1.1991   0.10148   0.09568  -0.0158   0.0503   1.0000
  16.000   1.1533   0.11236   0.10691  -0.0224   0.0514   1.0000
  16.250   1.1039   0.12608   0.12091  -0.0316   0.0529   1.0000
  16.500   1.0566   0.14186   0.13683  -0.0420   0.0550   1.0000
  16.750   1.0327   0.15340   0.14839  -0.0486   0.0563   1.0000
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