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


Details Polar file
Airfoil: CLARK X AIRFOIL (clarkx-il)
Reynolds number: 50,000
Max Cl/Cd: 36.38 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkx-il-50000-n5.txt
Download as CSV file: xf-clarkx-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4142   0.11311   0.10550  -0.0414   1.0000   0.0860
 -10.250  -0.4151   0.10912   0.10155  -0.0428   1.0000   0.0860
 -10.000  -0.4195   0.10497   0.09746  -0.0447   1.0000   0.0862
  -9.750  -0.4236   0.10088   0.09344  -0.0462   1.0000   0.0862
  -9.500  -0.4261   0.09706   0.08967  -0.0470   1.0000   0.0860
  -9.250  -0.4277   0.09354   0.08619  -0.0471   1.0000   0.0857
  -9.000  -0.4328   0.09008   0.08281  -0.0472   1.0000   0.0852
  -8.750  -0.4431   0.08668   0.07951  -0.0470   1.0000   0.0848
  -8.500  -0.4575   0.08320   0.07614  -0.0470   1.0000   0.0843
  -8.250  -0.4713   0.07920   0.07224  -0.0474   1.0000   0.0839
  -8.000  -0.4866   0.07502   0.06809  -0.0477   1.0000   0.0837
  -7.750  -0.5025   0.07062   0.06367  -0.0477   1.0000   0.0837
  -7.500  -0.5172   0.06607   0.05901  -0.0477   1.0000   0.0841
  -7.250  -0.5291   0.06133   0.05404  -0.0478   1.0000   0.0848
  -7.000  -0.5359   0.05661   0.04895  -0.0477   1.0000   0.0856
  -6.750  -0.5357   0.05239   0.04427  -0.0474   1.0000   0.0862
  -6.500  -0.5275   0.04951   0.04123  -0.0465   1.0000   0.0870
  -6.250  -0.5168   0.04694   0.03841  -0.0457   1.0000   0.0878
  -6.000  -0.5040   0.04462   0.03586  -0.0449   1.0000   0.0889
  -5.750  -0.4833   0.04243   0.03341  -0.0455   0.9979   0.0909
  -5.500  -0.4515   0.04007   0.03062  -0.0481   0.9924   0.0950
  -5.250  -0.4189   0.03743   0.02733  -0.0506   0.9868   0.0985
  -5.000  -0.3855   0.03522   0.02458  -0.0527   0.9814   0.1009
  -4.750  -0.3524   0.03380   0.02302  -0.0546   0.9757   0.1039
  -4.500  -0.3190   0.03268   0.02168  -0.0563   0.9698   0.1094
  -4.250  -0.2847   0.03147   0.02003  -0.0580   0.9636   0.1153
  -4.000  -0.2507   0.03047   0.01900  -0.0597   0.9580   0.1201
  -3.750  -0.2182   0.02964   0.01795  -0.0609   0.9511   0.1272
  -3.500  -0.1809   0.02888   0.01714  -0.0631   0.9460   0.1367
  -3.250  -0.1515   0.02823   0.01630  -0.0635   0.9380   0.1458
  -3.000  -0.1149   0.02758   0.01565  -0.0655   0.9324   0.1593
  -2.750  -0.0847   0.02706   0.01511  -0.0663   0.9247   0.1761
  -2.500  -0.0499   0.02649   0.01468  -0.0679   0.9182   0.1986
  -2.250  -0.0177   0.02603   0.01437  -0.0691   0.9110   0.2381
  -2.000   0.0144   0.02553   0.01413  -0.0703   0.9036   0.2998
  -1.750   0.0471   0.02491   0.01393  -0.0716   0.8971   0.3874
  -1.500   0.0733   0.02428   0.01388  -0.0713   0.8888   0.5050
  -1.250   0.1031   0.02338   0.01399  -0.0699   0.8842   0.7446
  -1.000   0.1597   0.02324   0.01389  -0.0748   0.8767   1.0000
  -0.750   0.1974   0.02331   0.01366  -0.0768   0.8699   1.0000
  -0.500   0.2217   0.02351   0.01363  -0.0764   0.8592   1.0000
  -0.250   0.2553   0.02360   0.01351  -0.0776   0.8516   1.0000
   0.250   0.3099   0.02394   0.01353  -0.0776   0.8318   1.0000
   0.500   0.3448   0.02396   0.01340  -0.0787   0.8243   1.0000
   0.750   0.3684   0.02419   0.01353  -0.0780   0.8129   1.0000
   1.000   0.3982   0.02429   0.01352  -0.0782   0.8038   1.0000
   1.250   0.4287   0.02434   0.01349  -0.0784   0.7944   1.0000
   1.500   0.4532   0.02454   0.01363  -0.0777   0.7829   1.0000
   1.750   0.4842   0.02455   0.01358  -0.0779   0.7738   1.0000
   2.000   0.5126   0.02461   0.01359  -0.0777   0.7633   1.0000
   2.250   0.5369   0.02480   0.01376  -0.0769   0.7513   1.0000
   2.500   0.5652   0.02486   0.01380  -0.0766   0.7408   1.0000
   2.750   0.5962   0.02481   0.01373  -0.0766   0.7310   1.0000
   3.000   0.6196   0.02502   0.01395  -0.0757   0.7182   1.0000
   3.250   0.6449   0.02517   0.01410  -0.0749   0.7059   1.0000
   3.500   0.6729   0.02520   0.01415  -0.0744   0.6944   1.0000
   3.750   0.7037   0.02509   0.01405  -0.0742   0.6834   1.0000
   4.000   0.7274   0.02526   0.01426  -0.0732   0.6694   1.0000
   4.250   0.7518   0.02541   0.01446  -0.0722   0.6552   1.0000
   4.500   0.7766   0.02552   0.01460  -0.0712   0.6406   1.0000
   4.750   0.8015   0.02561   0.01474  -0.0702   0.6255   1.0000
   5.000   0.8265   0.02570   0.01489  -0.0692   0.6098   1.0000
   5.250   0.8513   0.02580   0.01502  -0.0682   0.5937   1.0000
   5.500   0.8759   0.02592   0.01518  -0.0671   0.5772   1.0000
   5.750   0.9005   0.02607   0.01538  -0.0661   0.5605   1.0000
   6.000   0.9247   0.02627   0.01561  -0.0650   0.5435   1.0000
   6.250   0.9458   0.02665   0.01605  -0.0637   0.5255   1.0000
   6.500   0.9675   0.02704   0.01651  -0.0624   0.5079   1.0000
   6.750   0.9892   0.02745   0.01700  -0.0612   0.4902   1.0000
   7.000   1.0109   0.02790   0.01751  -0.0600   0.4729   1.0000
   7.250   1.0325   0.02840   0.01806  -0.0588   0.4558   1.0000
   7.750   1.0747   0.02954   0.01936  -0.0563   0.4230   1.0000
   8.000   1.0951   0.03020   0.02010  -0.0551   0.4072   1.0000
   8.250   1.1150   0.03093   0.02091  -0.0538   0.3919   1.0000
   8.500   1.1343   0.03172   0.02181  -0.0526   0.3772   1.0000
   8.750   1.1529   0.03256   0.02279  -0.0512   0.3628   1.0000
   9.000   1.1696   0.03340   0.02373  -0.0496   0.3475   1.0000
   9.250   1.1824   0.03418   0.02455  -0.0474   0.3300   1.0000
   9.500   1.1877   0.03504   0.02542  -0.0444   0.3099   1.0000
   9.750   1.1861   0.03606   0.02649  -0.0406   0.2892   1.0000
  10.000   1.1839   0.03722   0.02761  -0.0371   0.2685   1.0000
  10.250   1.1821   0.03868   0.02913  -0.0342   0.2482   1.0000
  10.500   1.1817   0.04031   0.03085  -0.0318   0.2290   1.0000
  10.750   1.1804   0.04216   0.03273  -0.0297   0.2097   1.0000
  11.000   1.1774   0.04435   0.03497  -0.0278   0.1884   1.0000
  11.250   1.1724   0.04692   0.03755  -0.0263   0.1660   1.0000
  11.500   1.1662   0.04992   0.04055  -0.0251   0.1415   1.0000
  11.750   1.1580   0.05334   0.04388  -0.0242   0.1194   1.0000
  12.000   1.1494   0.05703   0.04749  -0.0236   0.1030   1.0000
  12.250   1.1406   0.06091   0.05129  -0.0233   0.0922   1.0000
  12.500   1.1314   0.06497   0.05528  -0.0232   0.0849   1.0000
  12.750   1.1258   0.06878   0.05915  -0.0231   0.0780   1.0000
  13.000   1.1189   0.07277   0.06313  -0.0232   0.0734   1.0000
  13.250   1.1154   0.07645   0.06690  -0.0231   0.0693   1.0000
  13.500   1.1128   0.08009   0.07070  -0.0232   0.0655   1.0000
  13.750   1.1097   0.08380   0.07445  -0.0235   0.0624   1.0000
  14.000   1.1079   0.08742   0.07813  -0.0237   0.0596   1.0000
  14.250   1.1070   0.09116   0.08210  -0.0241   0.0569   1.0000
  14.500   1.1062   0.09486   0.08595  -0.0245   0.0547   1.0000
  14.750   1.1065   0.09839   0.08958  -0.0249   0.0529   1.0000
  15.000   1.1087   0.10148   0.09269  -0.0250   0.0511   1.0000
  15.250   1.1067   0.10569   0.09707  -0.0259   0.0498   1.0000
  15.500   1.0996   0.11111   0.10278  -0.0278   0.0487   1.0000
  15.750   1.0904   0.11713   0.10907  -0.0304   0.0478   1.0000
  16.000   1.0787   0.12392   0.11610  -0.0337   0.0472   1.0000
  16.250   1.0635   0.13186   0.12427  -0.0380   0.0468   1.0000
  16.500   1.0420   0.14201   0.13467  -0.0439   0.0470   1.0000
  16.750   1.0136   0.15525   0.14807  -0.0519   0.0477   1.0000
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