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CLARK X AIRFOIL (clarkx-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 50,000
Max Cl/Cd: 32.86 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkx-il-50000.txt
Download as CSV file: xf-clarkx-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3648   0.10761   0.10039  -0.0260   1.0000   0.2852
  -8.500  -0.3449   0.10290   0.09567  -0.0249   1.0000   0.2931
  -8.250  -0.3774   0.10353   0.09651  -0.0240   1.0000   0.3021
  -8.000  -0.3494   0.09847   0.09141  -0.0226   1.0000   0.3149
  -7.750  -0.3461   0.09564   0.08864  -0.0211   1.0000   0.3257
  -7.500  -0.3847   0.09643   0.08966  -0.0180   1.0000   0.3344
  -7.250  -0.3718   0.09298   0.08623  -0.0160   1.0000   0.3495
  -7.000  -0.3593   0.08954   0.08282  -0.0142   1.0000   0.3617
  -6.750  -0.3703   0.08775   0.08114  -0.0110   1.0000   0.3721
  -6.500  -0.4104   0.08841   0.08202  -0.0052   1.0000   0.3828
  -6.250  -0.3964   0.08500   0.07861  -0.0032   1.0000   0.3965
  -6.000  -0.3989   0.08271   0.07639   0.0001   1.0000   0.4084
  -5.750  -0.4115   0.08108   0.07487   0.0040   1.0000   0.4223
  -5.500  -0.4183   0.07925   0.07312   0.0077   1.0000   0.4394
  -5.000  -0.4637   0.05622   0.04904  -0.0321   1.0000   0.2059
  -4.750  -0.4461   0.05028   0.04254  -0.0355   1.0000   0.1926
  -4.500  -0.4269   0.04679   0.03866  -0.0366   1.0000   0.1899
  -4.250  -0.4059   0.04360   0.03515  -0.0374   1.0000   0.1878
  -4.000  -0.3821   0.04057   0.03166  -0.0385   1.0000   0.1863
  -3.750  -0.3571   0.03812   0.02863  -0.0394   1.0000   0.1894
  -3.500  -0.3332   0.03620   0.02638  -0.0398   1.0000   0.1937
  -3.250  -0.3098   0.03474   0.02473  -0.0399   1.0000   0.1981
  -3.000  -0.2847   0.03340   0.02298  -0.0401   1.0000   0.2051
  -2.750  -0.2622   0.03244   0.02196  -0.0400   1.0000   0.2144
  -2.500  -0.2373   0.03147   0.02068  -0.0401   1.0000   0.2240
  -2.250  -0.2140   0.03085   0.01992  -0.0399   1.0000   0.2380
  -2.000  -0.1912   0.03030   0.01938  -0.0398   1.0000   0.2548
  -1.750  -0.1685   0.02979   0.01893  -0.0395   1.0000   0.2750
  -1.500  -0.1449   0.02938   0.01859  -0.0393   1.0000   0.3073
  -1.250  -0.1186   0.02879   0.01822  -0.0396   1.0000   0.3625
  -1.000  -0.0886   0.02720   0.01792  -0.0398   1.0000   0.5426
  -0.750  -0.0818   0.02572   0.01765  -0.0348   1.0000   1.0000
  -0.500  -0.0600   0.02636   0.01778  -0.0351   1.0000   1.0000
  -0.250  -0.0398   0.02704   0.01813  -0.0353   1.0000   1.0000
   0.000   0.0064   0.02827   0.01896  -0.0402   0.9894   1.0000
   0.250   0.0526   0.02950   0.01989  -0.0451   0.9768   1.0000
   0.500   0.0957   0.03064   0.02078  -0.0493   0.9638   1.0000
   0.750   0.1369   0.03173   0.02167  -0.0530   0.9504   1.0000
   1.000   0.1773   0.03278   0.02255  -0.0565   0.9369   1.0000
   1.250   0.2177   0.03380   0.02343  -0.0599   0.9230   1.0000
   1.500   0.2582   0.03477   0.02429  -0.0631   0.9091   1.0000
   1.750   0.2967   0.03567   0.02511  -0.0658   0.8949   1.0000
   2.000   0.3297   0.03650   0.02587  -0.0675   0.8800   1.0000
   2.250   0.3621   0.03731   0.02664  -0.0690   0.8650   1.0000
   2.500   0.3942   0.03811   0.02741  -0.0704   0.8499   1.0000
   2.750   0.4261   0.03888   0.02816  -0.0716   0.8346   1.0000
   3.000   0.4577   0.03963   0.02892  -0.0727   0.8192   1.0000
   3.250   0.4894   0.04033   0.02963  -0.0736   0.8037   1.0000
   3.500   0.5210   0.04097   0.03030  -0.0744   0.7880   1.0000
   3.750   0.5528   0.04156   0.03094  -0.0750   0.7721   1.0000
   4.000   0.5853   0.04205   0.03147  -0.0755   0.7562   1.0000
   4.250   0.6182   0.04243   0.03191  -0.0759   0.7402   1.0000
   4.500   0.6518   0.04266   0.03224  -0.0762   0.7241   1.0000
   4.750   0.6868   0.04268   0.03234  -0.0763   0.7081   1.0000
   5.000   0.7227   0.04250   0.03227  -0.0762   0.6922   1.0000
   5.250   0.7596   0.04211   0.03200  -0.0760   0.6764   1.0000
   5.500   0.7957   0.04161   0.03161  -0.0754   0.6607   1.0000
   5.750   0.8310   0.04106   0.03120  -0.0747   0.6450   1.0000
   6.000   0.8663   0.04047   0.03074  -0.0740   0.6293   1.0000
   6.250   0.9031   0.03974   0.03016  -0.0732   0.6134   1.0000
   6.500   0.9219   0.04037   0.03089  -0.0714   0.5950   1.0000
   6.750   0.9458   0.04064   0.03128  -0.0699   0.5774   1.0000
   7.000   0.9746   0.04060   0.03137  -0.0687   0.5604   1.0000
   7.250   1.0045   0.04053   0.03145  -0.0676   0.5435   1.0000
   7.500   1.0343   0.04054   0.03159  -0.0665   0.5267   1.0000
   7.750   1.0622   0.04080   0.03198  -0.0655   0.5103   1.0000
   8.000   1.0892   0.04119   0.03252  -0.0644   0.4940   1.0000
   8.250   1.1140   0.04179   0.03325  -0.0631   0.4780   1.0000
   8.500   1.1375   0.04251   0.03411  -0.0618   0.4622   1.0000
   8.750   1.1718   0.04219   0.03391  -0.0610   0.4443   1.0000
   9.000   1.1964   0.04191   0.03370  -0.0590   0.4222   1.0000
   9.250   1.2278   0.03951   0.03115  -0.0564   0.3882   1.0000
   9.500   1.2461   0.03847   0.02999  -0.0533   0.3576   1.0000
   9.750   1.2600   0.03835   0.02983  -0.0503   0.3302   1.0000
  10.000   1.2648   0.03861   0.03003  -0.0463   0.3003   1.0000
  10.250   1.2582   0.03943   0.03079  -0.0412   0.2672   1.0000
  10.500   1.2441   0.04075   0.03186  -0.0354   0.2313   1.0000
  10.750   1.2302   0.04285   0.03355  -0.0303   0.1967   1.0000
  11.000   1.2246   0.04525   0.03559  -0.0267   0.1694   1.0000
  11.250   1.2246   0.04793   0.03832  -0.0240   0.1503   1.0000
  11.500   1.2321   0.05041   0.04077  -0.0220   0.1361   1.0000
  11.750   1.2438   0.05281   0.04314  -0.0204   0.1250   1.0000
  12.000   1.2602   0.05533   0.04569  -0.0192   0.1165   1.0000
  12.250   1.2683   0.05861   0.04925  -0.0177   0.1113   1.0000
  12.500   1.2701   0.06175   0.05265  -0.0160   0.1070   1.0000
  12.750   1.2897   0.06472   0.05553  -0.0154   0.1017   1.0000
  13.000   1.2759   0.06870   0.05992  -0.0134   0.1007   1.0000
  13.250   1.2597   0.07313   0.06470  -0.0120   0.1001   1.0000
  13.500   1.2396   0.07806   0.06996  -0.0112   0.1000   1.0000
  13.750   1.2154   0.08360   0.07579  -0.0112   0.1001   1.0000
  14.000   1.1881   0.08989   0.08232  -0.0122   0.1006   1.0000
  14.250   1.1590   0.09698   0.08961  -0.0144   0.1013   1.0000
  14.500   1.1300   0.10484   0.09764  -0.0174   0.1020   1.0000
  14.750   0.9382   0.15435   0.14711  -0.0515   0.1298   1.0000
  15.000   0.9430   0.15912   0.15192  -0.0525   0.1285   1.0000
  15.250   0.8865   0.18397   0.17654  -0.0706   0.1873   1.0000
  15.500   0.9123   0.18284   0.17549  -0.0663   0.1564   1.0000
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