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CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il)
Reynolds number: 50,000
Max Cl/Cd: 35.34 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkysm-il-50000-n5.txt
Download as CSV file: xf-clarkysm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK-Y 11.7% smoothed                          
  
 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  -0.3642   0.11556   0.10804  -0.0438   1.0000   0.0678
 -10.250  -0.3642   0.11206   0.10461  -0.0442   1.0000   0.0676
 -10.000  -0.3647   0.10871   0.10132  -0.0445   1.0000   0.0675
  -9.750  -0.3659   0.10534   0.09803  -0.0446   1.0000   0.0673
  -9.500  -0.3674   0.10211   0.09486  -0.0445   1.0000   0.0669
  -9.250  -0.3703   0.09892   0.09174  -0.0443   1.0000   0.0664
  -9.000  -0.3754   0.09575   0.08867  -0.0441   1.0000   0.0659
  -8.750  -0.3834   0.09261   0.08562  -0.0437   1.0000   0.0654
  -8.500  -0.3950   0.08953   0.08266  -0.0432   1.0000   0.0649
  -8.250  -0.4104   0.08667   0.07992  -0.0422   1.0000   0.0644
  -8.000  -0.4305   0.08388   0.07726  -0.0409   1.0000   0.0639
  -7.750  -0.4483   0.08045   0.07394  -0.0404   1.0000   0.0634
  -7.500  -0.4648   0.07670   0.07023  -0.0401   1.0000   0.0630
  -7.250  -0.4798   0.07272   0.06626  -0.0397   1.0000   0.0629
  -7.000  -0.4926   0.06858   0.06206  -0.0393   1.0000   0.0631
  -6.750  -0.5022   0.06438   0.05773  -0.0388   1.0000   0.0634
  -6.500  -0.5088   0.06005   0.05319  -0.0384   1.0000   0.0643
  -6.250  -0.5098   0.05544   0.04823  -0.0385   0.9993   0.0653
  -6.000  -0.4908   0.04936   0.04143  -0.0422   0.9923   0.0669
  -5.750  -0.4683   0.04496   0.03639  -0.0444   0.9857   0.0686
  -5.500  -0.4413   0.04335   0.03472  -0.0458   0.9795   0.0720
  -5.250  -0.4143   0.04060   0.03146  -0.0473   0.9731   0.0762
  -5.000  -0.3874   0.03759   0.02760  -0.0482   0.9668   0.0800
  -4.750  -0.3587   0.03625   0.02625  -0.0493   0.9604   0.0848
  -4.500  -0.3282   0.03455   0.02412  -0.0503   0.9546   0.0904
  -4.250  -0.2999   0.03320   0.02253  -0.0509   0.9476   0.0968
  -4.000  -0.2649   0.03201   0.02106  -0.0525   0.9424   0.1047
  -3.750  -0.2391   0.03108   0.02001  -0.0525   0.9345   0.1125
  -3.500  -0.2043   0.03016   0.01882  -0.0538   0.9288   0.1232
  -3.250  -0.1762   0.02948   0.01813  -0.0541   0.9213   0.1342
  -3.000  -0.1425   0.02881   0.01739  -0.0553   0.9149   0.1482
  -2.750  -0.1090   0.02824   0.01675  -0.0565   0.9084   0.1656
  -2.500  -0.0785   0.02774   0.01625  -0.0572   0.9007   0.1873
  -2.250  -0.0425   0.02718   0.01579  -0.0588   0.8949   0.2201
  -2.000  -0.0170   0.02672   0.01549  -0.0587   0.8859   0.2634
  -1.750   0.0196   0.02601   0.01515  -0.0605   0.8805   0.3415
  -1.500   0.0397   0.02544   0.01506  -0.0592   0.8706   0.4414
  -1.250   0.0734   0.02426   0.01508  -0.0590   0.8658   0.7028
  -1.000   0.1810   0.02406   0.01483  -0.0738   0.8655   1.0000
  -0.500   0.2364   0.02426   0.01451  -0.0739   0.8459   1.0000
  -0.250   0.2662   0.02432   0.01437  -0.0742   0.8361   1.0000
   0.000   0.2916   0.02444   0.01431  -0.0737   0.8253   1.0000
   0.500   0.3536   0.02446   0.01401  -0.0744   0.8056   1.0000
   0.750   0.3803   0.02451   0.01393  -0.0740   0.7943   1.0000
   1.000   0.4199   0.02426   0.01356  -0.0755   0.7862   1.0000
   1.500   0.4671   0.02441   0.01353  -0.0733   0.7604   1.0000
   1.750   0.4956   0.02437   0.01341  -0.0729   0.7488   1.0000
   2.000   0.5308   0.02416   0.01312  -0.0735   0.7391   1.0000
   2.250   0.5532   0.02427   0.01319  -0.0722   0.7255   1.0000
   2.500   0.5772   0.02435   0.01323  -0.0711   0.7122   1.0000
   2.750   0.6028   0.02440   0.01324  -0.0703   0.6993   1.0000
   3.000   0.6304   0.02439   0.01320  -0.0697   0.6867   1.0000
   3.250   0.6605   0.02430   0.01307  -0.0695   0.6746   1.0000
   3.500   0.6864   0.02434   0.01310  -0.0687   0.6608   1.0000
   3.750   0.7098   0.02449   0.01324  -0.0675   0.6461   1.0000
   4.000   0.7336   0.02463   0.01337  -0.0664   0.6313   1.0000
   4.250   0.7576   0.02478   0.01351  -0.0653   0.6163   1.0000
   4.500   0.7816   0.02496   0.01371  -0.0643   0.6013   1.0000
   4.750   0.8054   0.02517   0.01391  -0.0632   0.5861   1.0000
   5.000   0.8290   0.02541   0.01415  -0.0622   0.5709   1.0000
   5.250   0.8524   0.02569   0.01445  -0.0611   0.5558   1.0000
   5.500   0.8756   0.02601   0.01478  -0.0601   0.5411   1.0000
   5.750   0.8987   0.02638   0.01515  -0.0590   0.5267   1.0000
   6.000   0.9219   0.02677   0.01556  -0.0581   0.5127   1.0000
   6.250   0.9458   0.02718   0.01600  -0.0572   0.4995   1.0000
   6.500   0.9710   0.02757   0.01640  -0.0566   0.4870   1.0000
   6.750   0.9911   0.02816   0.01706  -0.0553   0.4740   1.0000
   7.000   1.0110   0.02880   0.01780  -0.0540   0.4617   1.0000
   7.250   1.0325   0.02940   0.01846  -0.0530   0.4501   1.0000
   7.500   1.0565   0.02992   0.01901  -0.0522   0.4389   1.0000
   7.750   1.0761   0.03045   0.01959  -0.0508   0.4256   1.0000
   8.000   1.0916   0.03095   0.02013  -0.0487   0.4099   1.0000
   8.250   1.1041   0.03146   0.02063  -0.0461   0.3931   1.0000
   8.500   1.1137   0.03205   0.02126  -0.0432   0.3764   1.0000
   8.750   1.1242   0.03269   0.02192  -0.0406   0.3609   1.0000
   9.000   1.1364   0.03334   0.02263  -0.0383   0.3471   1.0000
   9.250   1.1430   0.03417   0.02357  -0.0353   0.3336   1.0000
   9.500   1.1491   0.03505   0.02454  -0.0323   0.3200   1.0000
   9.750   1.1545   0.03599   0.02556  -0.0294   0.3060   1.0000
  10.000   1.1591   0.03702   0.02667  -0.0266   0.2918   1.0000
  10.250   1.1624   0.03816   0.02792  -0.0238   0.2772   1.0000
  10.500   1.1639   0.03946   0.02929  -0.0212   0.2619   1.0000
  10.750   1.1642   0.04094   0.03084  -0.0186   0.2461   1.0000
  11.000   1.1637   0.04259   0.03256  -0.0163   0.2300   1.0000
  11.250   1.1624   0.04444   0.03445  -0.0142   0.2140   1.0000
  11.500   1.1608   0.04647   0.03649  -0.0124   0.1987   1.0000
  11.750   1.1595   0.04867   0.03870  -0.0109   0.1849   1.0000
  12.000   1.1589   0.05100   0.04106  -0.0096   0.1730   1.0000
  12.250   1.1588   0.05338   0.04344  -0.0085   0.1631   1.0000
  12.500   1.1592   0.05574   0.04574  -0.0075   0.1546   1.0000
  12.750   1.1590   0.05847   0.04858  -0.0067   0.1463   1.0000
  13.000   1.1615   0.06082   0.05086  -0.0060   0.1399   1.0000
  13.250   1.1620   0.06373   0.05396  -0.0055   0.1337   1.0000
  13.500   1.1664   0.06601   0.05620  -0.0049   0.1283   1.0000
  13.750   1.1654   0.06922   0.05960  -0.0047   0.1234   1.0000
  14.000   1.1656   0.07229   0.06283  -0.0046   0.1187   1.0000
  14.250   1.1766   0.07397   0.06441  -0.0038   0.1141   1.0000
  14.500   1.1678   0.07847   0.06924  -0.0045   0.1109   1.0000
  14.750   1.1603   0.08288   0.07388  -0.0053   0.1076   1.0000
  15.000   1.1600   0.08624   0.07734  -0.0056   0.1042   1.0000
  15.250   1.1674   0.08858   0.07967  -0.0054   0.1005   1.0000
  15.500   1.1463   0.09542   0.08684  -0.0079   0.0990   1.0000
  15.750   1.1195   0.10372   0.09543  -0.0116   0.0977   1.0000
  16.000   1.0804   0.11516   0.10714  -0.0176   0.0972   1.0000
  16.250   0.9983   0.13861   0.13071  -0.0312   0.0977   1.0000
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