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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=1


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: 64.18 at α=11.5°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-060-050-gn-1000000-n1.txt
Download as CSV file: xf-cp-060-050-gn-1000000-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 =     1.000 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.5882   0.20612   0.20376  -0.0110   0.9999   0.0187
 -17.250  -0.5799   0.20321   0.20085  -0.0130   0.9998   0.0191
  -8.750  -0.7614   0.01921   0.01453  -0.1268   0.8812   0.0473
  -8.500  -0.7434   0.01809   0.01326  -0.1258   0.8747   0.0476
  -8.250  -0.7230   0.01727   0.01232  -0.1250   0.8689   0.0479
  -8.000  -0.7015   0.01661   0.01154  -0.1242   0.8634   0.0482
  -7.750  -0.6791   0.01601   0.01085  -0.1235   0.8578   0.0484
  -7.500  -0.6561   0.01546   0.01022  -0.1228   0.8521   0.0486
  -7.250  -0.6328   0.01497   0.00965  -0.1221   0.8468   0.0489
  -7.000  -0.6092   0.01451   0.00910  -0.1214   0.8415   0.0492
  -6.750  -0.5849   0.01410   0.00862  -0.1208   0.8358   0.0494
  -6.500  -0.5594   0.01387   0.00837  -0.1203   0.8308   0.0496
  -6.250  -0.5344   0.01362   0.00807  -0.1198   0.8252   0.0498
  -6.000  -0.5090   0.01337   0.00777  -0.1192   0.8198   0.0500
  -5.750  -0.4834   0.01312   0.00749  -0.1187   0.8140   0.0501
  -5.500  -0.4579   0.01287   0.00720  -0.1181   0.8081   0.0503
  -5.250  -0.4325   0.01266   0.00694  -0.1175   0.8023   0.0505
  -5.000  -0.4067   0.01240   0.00664  -0.1170   0.7967   0.0507
  -4.750  -0.3812   0.01219   0.00639  -0.1164   0.7889   0.0509
  -4.500  -0.3572   0.01203   0.00615  -0.1154   0.7709   0.0512
  -4.250  -0.3359   0.01197   0.00592  -0.1138   0.7354   0.0514
  -4.000  -0.3157   0.01197   0.00572  -0.1120   0.6889   0.0517
  -3.750  -0.3137   0.01293   0.00576  -0.1067   0.4377   0.0520
  -3.500  -0.3052   0.01385   0.00577  -0.1029   0.0658   0.0522
  -3.250  -0.2796   0.01369   0.00555  -0.1023   0.0572   0.0525
  -3.000  -0.2540   0.01352   0.00533  -0.1016   0.0542   0.0527
  -2.750  -0.2282   0.01337   0.00514  -0.1009   0.0528   0.0529
  -2.500  -0.2024   0.01321   0.00494  -0.1002   0.0515   0.0530
  -2.250  -0.1766   0.01307   0.00476  -0.0995   0.0504   0.0532
  -2.000  -0.1508   0.01294   0.00459  -0.0988   0.0495   0.0534
  -1.750  -0.1249   0.01283   0.00445  -0.0981   0.0490   0.0535
  -1.500  -0.0988   0.01276   0.00435  -0.0973   0.0485   0.0537
  -1.250  -0.0728   0.01268   0.00425  -0.0966   0.0482   0.0539
  -1.000  -0.0468   0.01262   0.00416  -0.0959   0.0478   0.0541
  -0.750  -0.0209   0.01256   0.00408  -0.0951   0.0474   0.0543
  -0.500   0.0051   0.01250   0.00400  -0.0943   0.0470   0.0546
  -0.250   0.0309   0.01245   0.00393  -0.0935   0.0464   0.0550
   0.000   0.0567   0.01240   0.00385  -0.0927   0.0458   0.0553
   0.250   0.0825   0.01235   0.00378  -0.0918   0.0455   0.0556
   0.500   0.1081   0.01230   0.00370  -0.0910   0.0452   0.0559
   0.750   0.1337   0.01225   0.00364  -0.0900   0.0449   0.0561
   1.000   0.1592   0.01221   0.00358  -0.0891   0.0448   0.0563
   1.250   0.1846   0.01218   0.00352  -0.0882   0.0446   0.0565
   1.500   0.2100   0.01216   0.00348  -0.0872   0.0444   0.0567
   1.750   0.2353   0.01214   0.00344  -0.0862   0.0442   0.0569
   2.000   0.2605   0.01213   0.00342  -0.0852   0.0441   0.0571
   2.250   0.2857   0.01213   0.00340  -0.0842   0.0440   0.0572
   2.500   0.3108   0.01213   0.00339  -0.0831   0.0439   0.0574
   2.750   0.3358   0.01214   0.00339  -0.0820   0.0438   0.0575
   3.000   0.3607   0.01216   0.00340  -0.0809   0.0437   0.0577
   3.250   0.3856   0.01220   0.00344  -0.0798   0.0436   0.0580
   3.500   0.4104   0.01224   0.00348  -0.0787   0.0435   0.0583
   3.750   0.4350   0.01229   0.00352  -0.0775   0.0434   0.0585
   4.000   0.4595   0.01234   0.00357  -0.0763   0.0433   0.0587
   4.250   0.4838   0.01239   0.00362  -0.0750   0.0432   0.0588
   4.500   0.5080   0.01245   0.00368  -0.0738   0.0431   0.0591
   4.750   0.5320   0.01252   0.00375  -0.0724   0.0430   0.0593
   5.000   0.5558   0.01259   0.00382  -0.0711   0.0429   0.0594
   5.250   0.5795   0.01267   0.00390  -0.0697   0.0427   0.0597
   5.500   0.6030   0.01275   0.00399  -0.0683   0.0424   0.0599
   5.750   0.6263   0.01285   0.00408  -0.0668   0.0422   0.0602
   6.000   0.6492   0.01294   0.00418  -0.0653   0.0419   0.0606
   6.250   0.6713   0.01304   0.00428  -0.0636   0.0418   0.0609
   6.500   0.6928   0.01313   0.00438  -0.0617   0.0416   0.0610
   6.750   0.7141   0.01324   0.00450  -0.0598   0.0414   0.0613
   7.000   0.7353   0.01335   0.00462  -0.0580   0.0413   0.0613
   7.250   0.7566   0.01348   0.00475  -0.0561   0.0412   0.0615
   7.500   0.7778   0.01361   0.00490  -0.0542   0.0410   0.0616
   7.750   0.7989   0.01377   0.00506  -0.0524   0.0409   0.0618
   8.000   0.8200   0.01394   0.00524  -0.0505   0.0407   0.0619
   8.250   0.8412   0.01411   0.00542  -0.0487   0.0406   0.0619
   8.500   0.8622   0.01430   0.00562  -0.0468   0.0405   0.0621
   8.750   0.8834   0.01447   0.00579  -0.0450   0.0401   0.0622
   9.000   0.9040   0.01467   0.00601  -0.0431   0.0400   0.0623
   9.250   0.9247   0.01487   0.00623  -0.0412   0.0399   0.0625
   9.500   0.9453   0.01508   0.00645  -0.0393   0.0397   0.0626
   9.750   0.9655   0.01531   0.00670  -0.0373   0.0396   0.0629
  10.000   0.9855   0.01555   0.00696  -0.0354   0.0395   0.0632
  10.250   1.0053   0.01580   0.00723  -0.0334   0.0394   0.0635
  10.500   1.0250   0.01605   0.00751  -0.0314   0.0394   0.0641
  10.750   1.0446   0.01631   0.00779  -0.0294   0.0392   0.0645
  11.000   1.0638   0.01659   0.00810  -0.0274   0.0392   0.0650
  11.250   1.0828   0.01688   0.00841  -0.0254   0.0391   0.0651
  11.500   1.1020   0.01717   0.00873  -0.0234   0.0390   0.0655
  11.750   1.1206   0.01749   0.00907  -0.0213   0.0388   0.0658
  12.000   1.1390   0.01781   0.00942  -0.0193   0.0388   0.0663
  12.250   1.1574   0.01814   0.00979  -0.0172   0.0386   0.0663
  12.500   1.1755   0.01849   0.01017  -0.0152   0.0385   0.0671
  12.750   1.1933   0.01886   0.01056  -0.0131   0.0384   0.0675
  13.000   1.2109   0.01924   0.01097  -0.0110   0.0382   0.0680
  13.250   1.2285   0.01962   0.01140  -0.0090   0.0381   0.0695
  13.500   1.2459   0.02002   0.01182  -0.0069   0.0379   0.0704
  13.750   1.2630   0.02042   0.01226  -0.0049   0.0375   0.0714
  14.250   1.2967   0.02131   0.01322  -0.0008   0.0373   0.0752
  14.500   1.3132   0.02174   0.01370   0.0012   0.0369   0.0990
  15.250   1.4319   0.02254   0.01611  -0.0069   0.0363   1.0000
  15.500   1.4483   0.02314   0.01673  -0.0051   0.0362   1.0000
  15.750   1.4643   0.02374   0.01736  -0.0032   0.0361   1.0000
  16.000   1.4804   0.02436   0.01799  -0.0014   0.0360   1.0000
  16.250   1.4962   0.02500   0.01866   0.0004   0.0358   1.0000
  16.500   1.5113   0.02569   0.01937   0.0023   0.0358   1.0000
  16.750   1.5256   0.02645   0.02016   0.0041   0.0356   1.0000
  17.000   1.5399   0.02722   0.02097   0.0059   0.0355   1.0000
  17.250   1.5533   0.02806   0.02185   0.0078   0.0355   1.0000
  17.500   1.5667   0.02890   0.02273   0.0095   0.0354   1.0000
  17.750   1.5793   0.02982   0.02369   0.0113   0.0352   1.0000
  18.000   1.5920   0.03073   0.02464   0.0130   0.0350   1.0000
  18.250   1.6044   0.03169   0.02565   0.0147   0.0348   1.0000
  18.500   1.6161   0.03272   0.02671   0.0164   0.0345   1.0000
  18.750   1.6275   0.03378   0.02782   0.0180   0.0344   1.0000
  19.000   1.6379   0.03493   0.02903   0.0196   0.0342   1.0000
  19.250   1.6483   0.03612   0.03027   0.0211   0.0341   1.0000
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