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Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 50.01 at α=11°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-060-050-gn-500000-n1.txt
Download as CSV file: xf-cp-060-050-gn-500000-n1.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 =     0.500 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2762   0.10122   0.09794  -0.0679   0.9513   0.0336
  -7.750  -0.2676   0.09775   0.09446  -0.0703   0.9474   0.0342
  -7.500  -0.2596   0.09383   0.09052  -0.0734   0.9435   0.0348
  -7.250  -0.2453   0.09090   0.08759  -0.0763   0.9400   0.0351
  -7.000  -0.2290   0.08795   0.08463  -0.0797   0.9368   0.0355
  -6.750  -0.2137   0.08479   0.08147  -0.0832   0.9322   0.0361
  -6.500  -0.1947   0.08102   0.07767  -0.0884   0.9260   0.0368
  -6.250  -0.1368   0.07386   0.07020  -0.1062   0.8755   0.0379
  -6.000  -0.1259   0.07083   0.06704  -0.1092   0.8474   0.0384
  -5.750  -0.1204   0.06864   0.06467  -0.1099   0.8073   0.0387
  -5.500  -0.1369   0.06856   0.06366  -0.1044   0.5971   0.0388
  -5.250  -0.1497   0.06774   0.06203  -0.1015   0.3615   0.0394
  -5.000  -0.1608   0.06629   0.05998  -0.0997   0.0890   0.0399
  -4.750  -0.1721   0.06339   0.05716  -0.0997   0.1060   0.0403
  -4.500  -0.1867   0.05967   0.05348  -0.1009   0.1259   0.0409
  -4.250  -0.1969   0.05524   0.04897  -0.1028   0.1032   0.0416
  -4.000  -0.1956   0.05209   0.04571  -0.1036   0.0678   0.0420
  -3.750  -0.1878   0.04951   0.04307  -0.1041   0.0628   0.0425
  -3.500  -0.1798   0.04662   0.04009  -0.1045   0.0605   0.0433
  -3.250  -0.1737   0.04293   0.03626  -0.1048   0.0596   0.0442
  -3.000  -0.1712   0.03793   0.03101  -0.1048   0.0579   0.0454
  -2.750  -0.1564   0.03562   0.02857  -0.1042   0.0566   0.0458
  -2.500  -0.1400   0.03355   0.02636  -0.1034   0.0553   0.0463
  -2.250  -0.1461   0.02497   0.01701  -0.1012   0.0553   0.0494
  -2.000  -0.1256   0.02368   0.01558  -0.1001   0.0541   0.0497
  -1.750  -0.1054   0.02224   0.01395  -0.0990   0.0534   0.0503
  -1.500  -0.0867   0.02029   0.01172  -0.0976   0.0526   0.0516
  -1.250  -0.0679   0.01823   0.00933  -0.0961   0.0520   0.0528
  -1.000  -0.0458   0.01714   0.00802  -0.0950   0.0514   0.0534
  -0.750  -0.0211   0.01687   0.00768  -0.0941   0.0507   0.0537
  -0.500   0.0037   0.01662   0.00738  -0.0932   0.0502   0.0539
  -0.250   0.0285   0.01638   0.00707  -0.0923   0.0497   0.0542
   0.000   0.0533   0.01615   0.00678  -0.0913   0.0493   0.0546
   0.250   0.0780   0.01592   0.00649  -0.0904   0.0490   0.0551
   0.500   0.1027   0.01569   0.00620  -0.0894   0.0486   0.0557
   0.750   0.1273   0.01548   0.00593  -0.0884   0.0481   0.0560
   1.000   0.1520   0.01530   0.00570  -0.0874   0.0478   0.0563
   1.250   0.1766   0.01512   0.00548  -0.0863   0.0473   0.0567
   1.500   0.2011   0.01499   0.00530  -0.0852   0.0468   0.0569
   1.750   0.2256   0.01487   0.00514  -0.0841   0.0465   0.0572
   2.000   0.2500   0.01477   0.00501  -0.0830   0.0463   0.0575
   2.250   0.2743   0.01470   0.00491  -0.0818   0.0460   0.0577
   2.500   0.2986   0.01468   0.00487  -0.0807   0.0458   0.0579
   2.750   0.3229   0.01468   0.00486  -0.0795   0.0456   0.0582
   3.000   0.3470   0.01468   0.00485  -0.0783   0.0454   0.0585
   3.250   0.3709   0.01470   0.00485  -0.0770   0.0452   0.0589
   3.500   0.3947   0.01471   0.00485  -0.0757   0.0450   0.0593
   3.750   0.4183   0.01473   0.00486  -0.0744   0.0448   0.0594
   4.000   0.4417   0.01476   0.00488  -0.0730   0.0447   0.0597
   4.250   0.4649   0.01480   0.00491  -0.0716   0.0445   0.0599
   4.500   0.4880   0.01485   0.00495  -0.0701   0.0444   0.0602
   4.750   0.5108   0.01491   0.00501  -0.0686   0.0443   0.0604
   5.000   0.5335   0.01499   0.00508  -0.0671   0.0441   0.0607
   5.250   0.5559   0.01508   0.00516  -0.0655   0.0441   0.0611
   5.500   0.5778   0.01517   0.00526  -0.0638   0.0439   0.0615
   5.750   0.5989   0.01527   0.00536  -0.0620   0.0438   0.0617
   6.000   0.6198   0.01538   0.00548  -0.0601   0.0436   0.0620
   6.250   0.6406   0.01549   0.00560  -0.0582   0.0434   0.0621
   6.500   0.6613   0.01563   0.00575  -0.0563   0.0431   0.0623
   6.750   0.6819   0.01578   0.00592  -0.0543   0.0429   0.0625
   7.000   0.7023   0.01595   0.00611  -0.0524   0.0427   0.0626
   7.250   0.7228   0.01614   0.00631  -0.0505   0.0426   0.0628
   7.500   0.7434   0.01634   0.00654  -0.0486   0.0424   0.0629
   7.750   0.7638   0.01656   0.00678  -0.0467   0.0423   0.0632
   8.000   0.7840   0.01679   0.00703  -0.0448   0.0421   0.0633
   8.250   0.8042   0.01703   0.00729  -0.0428   0.0419   0.0635
   8.500   0.8242   0.01730   0.00757  -0.0409   0.0418   0.0638
   8.750   0.8442   0.01756   0.00786  -0.0390   0.0416   0.0640
   9.000   0.8639   0.01784   0.00816  -0.0370   0.0415   0.0642
   9.250   0.8836   0.01813   0.00847  -0.0351   0.0413   0.0646
   9.500   0.9034   0.01842   0.00878  -0.0332   0.0410   0.0651
   9.750   0.9229   0.01872   0.00911  -0.0313   0.0408   0.0657
  10.000   0.9425   0.01901   0.00943  -0.0294   0.0405   0.0662
  10.250   0.9618   0.01934   0.00978  -0.0274   0.0403   0.0665
  10.500   0.9808   0.01968   0.01014  -0.0255   0.0402   0.0667
  10.750   1.0000   0.02001   0.01050  -0.0236   0.0400   0.0671
  11.000   1.0187   0.02037   0.01089  -0.0216   0.0399   0.0675
  11.250   1.0373   0.02075   0.01130  -0.0197   0.0398   0.0677
  11.500   1.0558   0.02114   0.01171  -0.0178   0.0397   0.0682
  11.750   1.0736   0.02159   0.01221  -0.0158   0.0396   0.0688
  12.000   1.0914   0.02204   0.01270  -0.0138   0.0395   0.0694
  12.250   1.1090   0.02251   0.01321  -0.0118   0.0394   0.0698
  12.500   1.1265   0.02300   0.01375  -0.0099   0.0392   0.0709
  12.750   1.1436   0.02352   0.01432  -0.0079   0.0391   0.0716
  13.000   1.1605   0.02407   0.01492  -0.0059   0.0389   0.0726
  13.250   1.1774   0.02461   0.01551  -0.0040   0.0388   0.0761
  13.500   1.1940   0.02518   0.01615  -0.0020   0.0387   0.0796
  13.750   1.2102   0.02580   0.01683  -0.0001   0.0384   0.0849
  14.000   1.2735   0.02560   0.01827  -0.0078   0.0380   1.0000
  14.250   1.2894   0.02628   0.01898  -0.0059   0.0378   1.0000
  14.500   1.3054   0.02696   0.01970  -0.0041   0.0374   1.0000
  14.750   1.3208   0.02769   0.02047  -0.0022   0.0373   1.0000
  15.000   1.3357   0.02845   0.02127  -0.0003   0.0371   1.0000
  15.250   1.3504   0.02921   0.02208   0.0015   0.0369   1.0000
  15.500   1.3645   0.03005   0.02297   0.0034   0.0368   1.0000
  15.750   1.3780   0.03091   0.02388   0.0052   0.0367   1.0000
  16.000   1.3915   0.03179   0.02480   0.0071   0.0365   1.0000
  16.250   1.4041   0.03272   0.02578   0.0089   0.0364   1.0000
  16.500   1.4162   0.03370   0.02682   0.0107   0.0363   1.0000
  16.750   1.4280   0.03473   0.02791   0.0124   0.0361   1.0000
  17.000   1.4390   0.03580   0.02903   0.0141   0.0360   1.0000
  17.250   1.4495   0.03694   0.03024   0.0158   0.0359   1.0000
  17.500   1.4593   0.03815   0.03151   0.0175   0.0358   1.0000
  17.750   1.4687   0.03940   0.03283   0.0191   0.0357   1.0000
  18.000   1.4765   0.04085   0.03436   0.0206   0.0356   1.0000
  18.250   1.4834   0.04241   0.03601   0.0221   0.0355   1.0000
  18.500   1.4882   0.04422   0.03794   0.0236   0.0351   1.0000
  18.750   1.4928   0.04607   0.03989   0.0249   0.0350   1.0000
  19.000   1.4955   0.04814   0.04208   0.0261   0.0347   1.0000
  19.250   1.4981   0.05025   0.04429   0.0272   0.0346   1.0000
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