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Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 60.06 at α=13°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-060-050-gn-1000000-n5.txt
Download as CSV file: xf-cp-060-050-gn-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=6% T=5% R=2.11                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.2896   0.07437   0.07209  -0.0822   0.9719   0.0456
  -6.000  -0.2557   0.06957   0.06729  -0.0880   0.9626   0.0459
  -5.000  -0.3731   0.01564   0.01096  -0.1226   0.9181   0.0578
  -4.750  -0.3488   0.01538   0.01070  -0.1218   0.9125   0.0580
  -4.500  -0.3217   0.01516   0.01044  -0.1215   0.9048   0.0581
  -4.250  -0.2958   0.01490   0.01015  -0.1209   0.8967   0.0582
  -4.000  -0.2699   0.01469   0.00989  -0.1203   0.8871   0.0584
  -3.750  -0.2441   0.01445   0.00961  -0.1197   0.8777   0.0585
  -3.500  -0.2186   0.01422   0.00932  -0.1190   0.8662   0.0586
  -3.250  -0.1931   0.01397   0.00903  -0.1184   0.8578   0.0588
  -3.000  -0.1680   0.01374   0.00873  -0.1176   0.8457   0.0590
  -2.750  -0.1433   0.01353   0.00845  -0.1166   0.8306   0.0592
  -2.500  -0.1194   0.01327   0.00809  -0.1156   0.8131   0.0594
  -2.250  -0.0965   0.01302   0.00772  -0.1143   0.7906   0.0597
  -2.000  -0.0752   0.01284   0.00737  -0.1126   0.7605   0.0600
  -1.750  -0.0567   0.01274   0.00703  -0.1103   0.7112   0.0603
  -1.500  -0.0427   0.01286   0.00677  -0.1072   0.6279   0.0607
  -1.250  -0.0554   0.01471   0.00707  -0.0993   0.1857   0.0609
  -0.750  -0.0112   0.01455   0.00645  -0.0965   0.0664   0.0616
  -0.500   0.0140   0.01434   0.00616  -0.0956   0.0634   0.0619
  -0.250   0.0392   0.01418   0.00593  -0.0947   0.0614   0.0621
   0.000   0.0643   0.01400   0.00569  -0.0938   0.0598   0.0623
   0.250   0.0892   0.01378   0.00544  -0.0928   0.0589   0.0626
   0.500   0.1145   0.01366   0.00531  -0.0919   0.0580   0.0628
   0.750   0.1398   0.01357   0.00520  -0.0910   0.0573   0.0630
   1.000   0.1651   0.01350   0.00512  -0.0900   0.0566   0.0632
   1.250   0.1904   0.01346   0.00506  -0.0891   0.0560   0.0635
   1.500   0.2155   0.01341   0.00500  -0.0881   0.0555   0.0637
   1.750   0.2405   0.01340   0.00496  -0.0870   0.0550   0.0640
   2.000   0.2653   0.01338   0.00493  -0.0860   0.0545   0.0644
   2.250   0.2897   0.01338   0.00491  -0.0848   0.0539   0.0647
   2.500   0.3144   0.01335   0.00485  -0.0837   0.0537   0.0650
   2.750   0.3389   0.01331   0.00480  -0.0825   0.0535   0.0654
   3.000   0.3634   0.01328   0.00475  -0.0813   0.0532   0.0657
   3.250   0.3876   0.01328   0.00474  -0.0801   0.0530   0.0660
   3.500   0.4118   0.01327   0.00472  -0.0788   0.0527   0.0663
   3.750   0.4359   0.01328   0.00472  -0.0776   0.0523   0.0665
   4.000   0.4598   0.01331   0.00473  -0.0762   0.0519   0.0667
   4.250   0.4835   0.01335   0.00477  -0.0749   0.0516   0.0669
   4.500   0.5069   0.01338   0.00479  -0.0735   0.0513   0.0671
   4.750   0.5297   0.01337   0.00479  -0.0720   0.0511   0.0675
   5.000   0.5527   0.01343   0.00486  -0.0704   0.0508   0.0679
   5.250   0.5756   0.01351   0.00495  -0.0689   0.0506   0.0682
   5.500   0.5981   0.01361   0.00505  -0.0673   0.0503   0.0685
   5.750   0.6202   0.01371   0.00516  -0.0657   0.0501   0.0688
   6.000   0.6416   0.01382   0.00527  -0.0639   0.0499   0.0691
   6.250   0.6621   0.01393   0.00539  -0.0618   0.0497   0.0694
   6.500   0.6818   0.01407   0.00553  -0.0597   0.0494   0.0697
   6.750   0.7011   0.01425   0.00572  -0.0575   0.0492   0.0701
   7.000   0.7193   0.01451   0.00598  -0.0551   0.0488   0.0704
   7.250   0.7399   0.01465   0.00613  -0.0531   0.0487   0.0707
   7.500   0.7603   0.01483   0.00632  -0.0512   0.0485   0.0711
   7.750   0.7809   0.01502   0.00652  -0.0492   0.0484   0.0715
   8.000   0.8014   0.01524   0.00675  -0.0473   0.0483   0.0718
   8.250   0.8219   0.01545   0.00698  -0.0454   0.0481   0.0720
   8.500   0.8418   0.01567   0.00722  -0.0434   0.0480   0.0724
   8.750   0.8620   0.01590   0.00747  -0.0414   0.0478   0.0729
   9.000   0.8819   0.01617   0.00776  -0.0394   0.0476   0.0732
   9.250   0.9020   0.01642   0.00804  -0.0375   0.0474   0.0737
   9.500   0.9218   0.01671   0.00835  -0.0355   0.0473   0.0742
   9.750   0.9415   0.01700   0.00867  -0.0335   0.0471   0.0748
  10.000   0.9614   0.01728   0.00897  -0.0316   0.0468   0.0753
  10.250   0.9811   0.01760   0.00931  -0.0297   0.0467   0.0759
  10.500   1.0005   0.01793   0.00966  -0.0277   0.0465   0.0766
  10.750   1.0200   0.01823   0.00998  -0.0258   0.0463   0.0773
  11.000   1.0392   0.01855   0.01033  -0.0238   0.0461   0.0782
  11.250   1.0585   0.01888   0.01068  -0.0219   0.0459   0.0792
  11.500   1.0776   0.01920   0.01102  -0.0200   0.0457   0.0813
  11.750   1.0963   0.01952   0.01137  -0.0180   0.0455   0.0833
  12.000   1.1148   0.01988   0.01176  -0.0160   0.0453   0.0863
  12.500   1.1512   0.02065   0.01260  -0.0120   0.0450   0.1081
  13.000   1.2457   0.02074   0.01438  -0.0205   0.0445   1.0000
  13.250   1.2634   0.02137   0.01502  -0.0186   0.0443   1.0000
  13.500   1.2808   0.02210   0.01576  -0.0167   0.0441   1.0000
  13.750   1.2985   0.02261   0.01630  -0.0148   0.0440   1.0000
  14.000   1.3161   0.02315   0.01687  -0.0129   0.0439   1.0000
  14.250   1.3332   0.02372   0.01747  -0.0110   0.0438   1.0000
  14.500   1.3500   0.02429   0.01807  -0.0091   0.0437   1.0000
  14.750   1.3665   0.02492   0.01874  -0.0072   0.0436   1.0000
  15.000   1.3825   0.02556   0.01943  -0.0053   0.0434   1.0000
  15.250   1.3980   0.02624   0.02015  -0.0034   0.0432   1.0000
  15.500   1.4133   0.02692   0.02088  -0.0015   0.0431   1.0000
  15.750   1.4281   0.02764   0.02163   0.0004   0.0429   1.0000
  16.000   1.4423   0.02840   0.02244   0.0023   0.0427   1.0000
  16.250   1.4561   0.02922   0.02331   0.0042   0.0425   1.0000
  16.500   1.4692   0.03010   0.02424   0.0061   0.0423   1.0000
  16.750   1.4819   0.03098   0.02518   0.0080   0.0422   1.0000
  17.000   1.4942   0.03191   0.02615   0.0099   0.0420   1.0000
  17.250   1.5055   0.03293   0.02723   0.0117   0.0419   1.0000
  17.500   1.5167   0.03397   0.02833   0.0135   0.0417   1.0000
  17.750   1.5270   0.03505   0.02946   0.0153   0.0416   1.0000
  18.000   1.5373   0.03614   0.03059   0.0170   0.0414   1.0000
  18.250   1.5466   0.03734   0.03185   0.0187   0.0413   1.0000
  18.500   1.5558   0.03857   0.03314   0.0203   0.0412   1.0000
  18.750   1.5638   0.03990   0.03453   0.0218   0.0411   1.0000
  19.000   1.5718   0.04128   0.03596   0.0233   0.0410   1.0000
  19.250   1.5787   0.04280   0.03753   0.0246   0.0409   1.0000
  19.500   1.5854   0.04437   0.03916   0.0259   0.0408   1.0000
  19.750   1.5919   0.04597   0.04082   0.0271   0.0407   1.0000
  20.000   1.5970   0.04777   0.04268   0.0281   0.0406   1.0000
  20.250   1.6027   0.04956   0.04452   0.0291   0.0405   1.0000
  20.500   1.6071   0.05153   0.04656   0.0299   0.0404   1.0000
  20.750   1.6113   0.05359   0.04867   0.0305   0.0403   1.0000
  21.000   1.6139   0.05587   0.05102   0.0311   0.0402   1.0000
  21.250   1.6164   0.05820   0.05341   0.0314   0.0401   1.0000
  21.500   1.6167   0.06088   0.05616   0.0316   0.0400   1.0000
  21.750   1.6152   0.06384   0.05920   0.0316   0.0399   1.0000
  22.000   1.6106   0.06725   0.06270   0.0313   0.0398   1.0000
  22.250   1.6051   0.07091   0.06648   0.0306   0.0397   1.0000
  22.500   1.5970   0.07502   0.07072   0.0296   0.0396   1.0000
  22.750   1.5876   0.07946   0.07529   0.0282   0.0395   1.0000
  23.000   1.5745   0.08457   0.08055   0.0263   0.0394   1.0000
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