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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 42.79 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-500000.txt
Download as CSV file: xf-cp-100-050-gn-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=10% T=5% R=1.3                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500   0.0171   0.10357   0.10063  -0.1252   0.9536   0.0356
  -8.250   0.0308   0.10112   0.09819  -0.1271   0.9514   0.0360
  -8.000   0.0471   0.09844   0.09550  -0.1298   0.9500   0.0366
  -7.750   0.0644   0.09559   0.09264  -0.1329   0.9489   0.0374
  -7.500   0.0823   0.09257   0.08961  -0.1374   0.9477   0.0382
  -7.250   0.0990   0.08990   0.08692  -0.1442   0.9464   0.0383
  -7.000   0.1206   0.08631   0.08332  -0.1460   0.9460   0.0385
  -6.750   0.1433   0.08335   0.08036  -0.1490   0.9454   0.0387
  -6.500   0.1500   0.08173   0.07875  -0.1484   0.9404   0.0389
  -6.250   0.1636   0.07968   0.07671  -0.1497   0.9367   0.0393
  -6.000   0.1843   0.07720   0.07422  -0.1530   0.9348   0.0399
  -5.750   0.2068   0.07454   0.07155  -0.1571   0.9330   0.0407
  -5.500   0.2304   0.07179   0.06877  -0.1633   0.9306   0.0418
  -5.250   0.2197   0.07134   0.06832  -0.1626   0.9200   0.0419
  -5.000   0.2398   0.06822   0.06520  -0.1651   0.9177   0.0421
  -4.750   0.2623   0.06548   0.06245  -0.1669   0.9160   0.0422
  -4.500   0.2866   0.06304   0.06000  -0.1698   0.9142   0.0425
  -4.250   0.2860   0.06207   0.05905  -0.1669   0.9071   0.0427
  -4.000   0.3025   0.06022   0.05720  -0.1684   0.9029   0.0432
  -3.750   0.3262   0.05806   0.05502  -0.1718   0.8999   0.0439
  -3.500   0.3541   0.05567   0.05259  -0.1767   0.8971   0.0452
  -3.250   0.3655   0.05447   0.05132  -0.1813   0.8877   0.0458
  -3.000   0.3874   0.05177   0.04861  -0.1835   0.8845   0.0459
  -2.750   0.4088   0.04947   0.04630  -0.1840   0.8821   0.0461
  -2.500   0.4261   0.04776   0.04460  -0.1841   0.8776   0.0463
  -2.250   0.4389   0.04634   0.04318  -0.1832   0.8709   0.0467
  -2.000   0.4674   0.04438   0.04118  -0.1860   0.8660   0.0474
  -1.750   0.4906   0.04260   0.03935  -0.1876   0.8591   0.0483
  -1.500   0.5385   0.03979   0.03634  -0.1973   0.8525   0.0501
  -1.250   0.5619   0.03764   0.03415  -0.1979   0.8461   0.0503
  -1.000   0.5720   0.03640   0.03295  -0.1953   0.8384   0.0505
  -0.750   0.5954   0.03491   0.03141  -0.1958   0.8304   0.0509
  -0.500   0.6150   0.03367   0.03016  -0.1954   0.8226   0.0516
  -0.250   0.6400   0.03223   0.02866  -0.1962   0.8142   0.0526
   0.000   0.6853   0.02955   0.02574  -0.2019   0.8067   0.0550
   0.250   0.7025   0.02834   0.02447  -0.2005   0.7926   0.0552
   0.500   0.7170   0.02737   0.02345  -0.1983   0.7751   0.0555
   0.750   0.7275   0.02657   0.02257  -0.1950   0.7493   0.0560
   1.000   0.7287   0.02613   0.02186  -0.1895   0.6990   0.0565
   1.250   0.7146   0.02606   0.02146  -0.1807   0.6372   0.0570
   1.500   0.6913   0.02653   0.02147  -0.1703   0.5487   0.0572
   1.750   0.6640   0.02774   0.02199  -0.1598   0.4083   0.0573
   2.000   0.6370   0.02964   0.02295  -0.1501   0.1754   0.0575
   2.250   0.6617   0.02861   0.02126  -0.1499   0.0599   0.0603
   2.500   0.6793   0.02807   0.02072  -0.1485   0.0542   0.0606
   2.750   0.6983   0.02766   0.02029  -0.1473   0.0513   0.0611
   3.000   0.7198   0.02721   0.01982  -0.1465   0.0500   0.0619
   3.250   0.7432   0.02669   0.01923  -0.1459   0.0490   0.0637
   3.500   0.7728   0.02550   0.01781  -0.1460   0.0480   0.0666
   3.750   0.7907   0.02536   0.01766  -0.1444   0.0468   0.0674
   4.000   0.8092   0.02523   0.01748  -0.1429   0.0459   0.0686
   4.250   0.8338   0.02451   0.01648  -0.1418   0.0453   0.0731
   4.500   0.8480   0.02464   0.01665  -0.1395   0.0448   0.0737
   4.750   0.8644   0.02472   0.01672  -0.1376   0.0446   0.0747
   5.000   0.8822   0.02476   0.01672  -0.1358   0.0443   0.0769
   5.250   0.9015   0.02458   0.01637  -0.1340   0.0441   0.0814
   5.500   0.9166   0.02483   0.01665  -0.1319   0.0438   0.0829
   5.750   0.9346   0.02506   0.01669  -0.1298   0.0435   0.0895
   6.000   0.9493   0.02524   0.01690  -0.1276   0.0433   0.0906
   6.250   0.9641   0.02561   0.01730  -0.1255   0.0431   0.0926
   6.500   0.9804   0.02604   0.01761  -0.1233   0.0427   0.1001
   6.750   0.9957   0.02636   0.01796  -0.1213   0.0423   0.1020
   7.000   1.0116   0.02689   0.01847  -0.1193   0.0419   0.1065
   7.250   1.0285   0.02727   0.01880  -0.1175   0.0415   0.1136
   7.500   1.0455   0.02789   0.01937  -0.1156   0.0411   0.1245
   7.750   1.0635   0.02830   0.01982  -0.1141   0.0409   0.1295
   8.000   1.0833   0.02879   0.02029  -0.1127   0.0407   0.1419
   8.250   1.1103   0.02819   0.01914  -0.1106   0.0406   0.0734
   8.500   1.1337   0.02869   0.01964  -0.1097   0.0404   0.0738
   8.750   1.1596   0.02922   0.02018  -0.1090   0.0403   0.0748
   9.000   1.1892   0.02975   0.02070  -0.1089   0.0403   0.0754
   9.250   1.2223   0.03031   0.02127  -0.1094   0.0401   0.0759
   9.500   1.2579   0.03096   0.02192  -0.1102   0.0400   0.0770
   9.750   1.3101   0.03195   0.02285  -0.1139   0.0394   0.0788
  10.000   1.3422   0.03276   0.02377  -0.1141   0.0398   0.0811
  10.250   1.5624   0.04571   0.03836  -0.1484   0.0515   1.0000
  10.500   1.5062   0.03520   0.02852  -0.1326   0.0507   1.0000
  10.750   1.4998   0.03538   0.02896  -0.1260   0.0490   1.0000
  11.000   1.5113   0.03697   0.03067  -0.1233   0.0479   1.0000
  11.250   1.5251   0.03877   0.03253  -0.1212   0.0470   1.0000
  11.500   1.5411   0.04075   0.03455  -0.1196   0.0465   1.0000
  11.750   1.5606   0.04304   0.03685  -0.1188   0.0459   1.0000
  13.000   1.5129   0.05525   0.05014  -0.0917   0.0422   1.0000
  13.250   1.5020   0.05786   0.05291  -0.0871   0.0417   1.0000
  13.500   1.4906   0.06069   0.05590  -0.0829   0.0413   1.0000
  13.750   1.4783   0.06373   0.05909  -0.0789   0.0410   1.0000
  14.000   1.4651   0.06697   0.06247  -0.0753   0.0407   1.0000
  14.250   1.4510   0.07043   0.06607  -0.0720   0.0405   1.0000
  14.500   1.4356   0.07408   0.06986  -0.0690   0.0403   1.0000
  14.750   1.4195   0.07790   0.07381  -0.0664   0.0401   1.0000
  15.000   1.3986   0.08209   0.07816  -0.0640   0.0400   1.0000
  15.250   1.3747   0.08640   0.08263  -0.0621   0.0399   1.0000
  15.500   1.3101   0.09212   0.08871  -0.0602   0.0400   1.0000
  15.750   1.2658   0.09783   0.09467  -0.0603   0.0400   1.0000
  16.000   1.2153   0.10529   0.10240  -0.0623   0.0401   1.0000
  16.250   1.1711   0.11326   0.11059  -0.0657   0.0400   1.0000
  16.500   1.0610   0.13498   0.13278  -0.0806   0.0405   1.0000
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