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Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=100,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
Reynolds number: 100,000
Max Cl/Cd: 27.96 at α=10°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-060-050-gn-100000-n1.txt
Download as CSV file: xf-cp-060-050-gn-100000-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 =     0.100 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2571   0.10591   0.09922  -0.0524   0.9485   0.0403
  -6.500  -0.2498   0.10315   0.09647  -0.0536   0.9438   0.0406
  -6.250  -0.2415   0.10031   0.09366  -0.0551   0.9396   0.0409
  -6.000  -0.2338   0.09724   0.09059  -0.0569   0.9353   0.0415
  -5.750  -0.2272   0.09462   0.08800  -0.0579   0.9296   0.0421
  -5.500  -0.2184   0.09202   0.08543  -0.0593   0.9246   0.0426
  -5.250  -0.2085   0.08924   0.08266  -0.0612   0.9200   0.0433
  -5.000  -0.2021   0.08663   0.08008  -0.0623   0.9137   0.0436
  -4.750  -0.1946   0.08392   0.07739  -0.0638   0.9076   0.0439
  -4.500  -0.1853   0.08103   0.07451  -0.0659   0.9023   0.0442
  -4.250  -0.1813   0.07831   0.07182  -0.0671   0.8948   0.0447
  -4.000  -0.1782   0.07513   0.06864  -0.0691   0.8872   0.0455
  -3.750  -0.1727   0.07266   0.06621  -0.0705   0.8799   0.0460
  -3.500  -0.1709   0.07016   0.06373  -0.0714   0.8707   0.0465
  -3.250  -0.1621   0.06715   0.06071  -0.0739   0.8639   0.0469
  -3.000  -0.1578   0.06444   0.05799  -0.0751   0.8551   0.0473
  -2.750  -0.1486   0.06150   0.05502  -0.0770   0.8477   0.0476
  -2.500  -0.1384   0.05854   0.05202  -0.0788   0.8407   0.0480
  -2.250  -0.1300   0.05543   0.04884  -0.0801   0.8325   0.0489
  -2.000  -0.1157   0.05244   0.04577  -0.0818   0.8260   0.0497
  -1.750  -0.1008   0.05014   0.04341  -0.0825   0.8194   0.0503
  -1.500  -0.0847   0.04777   0.04095  -0.0830   0.8099   0.0508
  -1.250  -0.0643   0.04528   0.03832  -0.0840   0.7960   0.0512
  -1.000  -0.0389   0.04268   0.03552  -0.0856   0.7712   0.0516
  -0.750  -0.0052   0.03951   0.03191  -0.0887   0.7226   0.0529
  -0.500   0.0091   0.03923   0.02959  -0.0871   0.3297   0.0538
   0.000   0.0398   0.03756   0.02675  -0.0846   0.0732   0.0547
   0.250   0.0597   0.03608   0.02509  -0.0837   0.0698   0.0551
   0.500   0.0802   0.03464   0.02347  -0.0828   0.0672   0.0555
   0.750   0.1010   0.03301   0.02160  -0.0818   0.0654   0.0567
   1.250   0.1443   0.03041   0.01860  -0.0796   0.0628   0.0584
   1.500   0.1665   0.02952   0.01756  -0.0784   0.0615   0.0588
   1.750   0.1889   0.02869   0.01656  -0.0772   0.0602   0.0592
   2.000   0.2115   0.02792   0.01562  -0.0760   0.0590   0.0597
   2.250   0.2345   0.02708   0.01459  -0.0748   0.0578   0.0608
   2.500   0.2577   0.02613   0.01339  -0.0735   0.0569   0.0621
   2.750   0.2808   0.02577   0.01295  -0.0722   0.0561   0.0626
   3.000   0.3037   0.02547   0.01258  -0.0709   0.0557   0.0629
   3.250   0.3266   0.02520   0.01224  -0.0696   0.0552   0.0632
   3.500   0.3493   0.02497   0.01195  -0.0682   0.0548   0.0635
   3.750   0.3719   0.02479   0.01172  -0.0668   0.0545   0.0640
   4.000   0.3943   0.02464   0.01152  -0.0654   0.0542   0.0648
   4.250   0.4165   0.02452   0.01134  -0.0639   0.0539   0.0657
   4.500   0.4384   0.02443   0.01120  -0.0623   0.0536   0.0664
   4.750   0.4601   0.02439   0.01114  -0.0607   0.0531   0.0668
   5.000   0.4814   0.02440   0.01117  -0.0591   0.0526   0.0671
   5.250   0.5024   0.02448   0.01126  -0.0574   0.0520   0.0673
   5.500   0.5232   0.02459   0.01139  -0.0557   0.0514   0.0676
   5.750   0.5437   0.02473   0.01155  -0.0539   0.0509   0.0678
   6.000   0.5638   0.02489   0.01172  -0.0521   0.0503   0.0682
   6.250   0.5836   0.02509   0.01194  -0.0502   0.0500   0.0687
   6.500   0.6035   0.02533   0.01218  -0.0484   0.0497   0.0695
   6.750   0.6235   0.02560   0.01245  -0.0466   0.0495   0.0705
   7.000   0.6436   0.02590   0.01274  -0.0448   0.0493   0.0712
   7.250   0.6635   0.02623   0.01306  -0.0429   0.0491   0.0718
   7.500   0.6840   0.02660   0.01343  -0.0413   0.0489   0.0722
   7.750   0.7052   0.02701   0.01383  -0.0397   0.0487   0.0725
   8.000   0.7268   0.02749   0.01432  -0.0383   0.0485   0.0728
   8.250   0.7488   0.02799   0.01484  -0.0369   0.0482   0.0732
   8.500   0.7713   0.02853   0.01540  -0.0356   0.0479   0.0736
   8.750   0.7941   0.02911   0.01600  -0.0344   0.0474   0.0741
   9.000   0.8171   0.02972   0.01665  -0.0332   0.0470   0.0751
   9.250   0.8401   0.03035   0.01731  -0.0321   0.0464   0.0765
   9.500   0.8628   0.03102   0.01802  -0.0309   0.0460   0.0779
   9.750   0.8854   0.03172   0.01877  -0.0297   0.0456   0.0794
  10.000   0.9077   0.03246   0.01957  -0.0286   0.0454   0.0806
  10.250   0.9296   0.03325   0.02040  -0.0273   0.0451   0.0818
  10.500   0.9510   0.03407   0.02129  -0.0260   0.0449   0.0837
  10.750   0.9715   0.03491   0.02222  -0.0246   0.0447   0.0861
  11.000   0.9911   0.03578   0.02316  -0.0231   0.0445   0.0889
  11.250   1.0095   0.03665   0.02412  -0.0215   0.0442   0.0928
  11.500   1.0285   0.03773   0.02533  -0.0200   0.0439   0.0984
  11.750   1.0485   0.03905   0.02704  -0.0189   0.0432   0.1767
  12.500   1.1032   0.04272   0.03267  -0.0158   0.0417   1.0000
  12.750   1.1114   0.04436   0.03446  -0.0132   0.0415   1.0000
  13.000   1.1172   0.04611   0.03639  -0.0106   0.0412   1.0000
  13.250   1.1205   0.04796   0.03841  -0.0078   0.0410   1.0000
  13.500   1.1214   0.04995   0.04058  -0.0051   0.0408   1.0000
  13.750   1.1194   0.05213   0.04294  -0.0024   0.0405   1.0000
  14.000   1.1152   0.05445   0.04545   0.0002   0.0403   1.0000
  14.250   1.1083   0.05702   0.04820   0.0025   0.0401   1.0000
  14.500   1.0988   0.05984   0.05122   0.0045   0.0398   1.0000
  14.750   1.0760   0.06435   0.05603   0.0060   0.0395   1.0000
  15.000   1.0384   0.07091   0.06297   0.0060   0.0391   1.0000
  15.250   0.9738   0.08220   0.07476   0.0016   0.0386   1.0000
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