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Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 57.94 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-1000000-n5.txt
Download as CSV file: xf-cp-080-050-gn-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=8% T=5% R=1.6                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1275   0.09958   0.09734  -0.1022   0.9694   0.0285
  -8.500  -0.1190   0.09743   0.09520  -0.1029   0.9654   0.0288
  -8.000  -0.1067   0.08873   0.08645  -0.1092   0.9600   0.0308
  -7.750  -0.0882   0.08662   0.08434  -0.1119   0.9583   0.0309
  -7.500  -0.0696   0.08417   0.08189  -0.1150   0.9567   0.0311
  -7.250  -0.0553   0.08230   0.08003  -0.1165   0.9526   0.0313
  -7.000  -0.0361   0.08012   0.07783  -0.1194   0.9473   0.0315
  -6.750  -0.0206   0.07744   0.07515  -0.1224   0.9458   0.0317
  -6.250   0.0115   0.06858   0.06622  -0.1343   0.9379   0.0340
  -6.000   0.0398   0.06654   0.06414  -0.1388   0.9281   0.0342
  -5.750   0.0584   0.06452   0.06211  -0.1416   0.9229   0.0344
  -5.500   0.0724   0.06261   0.06018  -0.1434   0.9143   0.0346
  -4.500   0.1001   0.05116   0.04856  -0.1522   0.8785   0.0374
  -4.250   0.1159   0.04958   0.04694  -0.1532   0.8717   0.0376
  -4.000   0.1313   0.04825   0.04558  -0.1536   0.8616   0.0377
  -3.750   0.1472   0.04662   0.04390  -0.1544   0.8529   0.0379
  -3.500   0.1636   0.04530   0.04253  -0.1547   0.8410   0.0381
  -3.250   0.1799   0.04367   0.04085  -0.1553   0.8297   0.0385
  -2.750   0.2082   0.03569   0.03261  -0.1602   0.8117   0.0411
  -2.500   0.2273   0.03453   0.03136  -0.1599   0.7971   0.0412
  -1.500   0.2844   0.01350   0.00877  -0.1619   0.7633   0.0487
  -1.250   0.3053   0.01325   0.00839  -0.1602   0.7412   0.0488
  -1.000   0.3257   0.01322   0.00825  -0.1584   0.7137   0.0490
  -0.750   0.3410   0.01330   0.00809  -0.1555   0.6684   0.0491
  -0.500   0.3520   0.01353   0.00799  -0.1517   0.5977   0.0492
  -0.250   0.3367   0.01511   0.00845  -0.1430   0.3339   0.0492
   0.250   0.3581   0.01604   0.00842  -0.1359   0.0496   0.0496
   0.500   0.3810   0.01573   0.00803  -0.1347   0.0468   0.0499
   0.750   0.4035   0.01540   0.00759  -0.1334   0.0442   0.0502
   1.000   0.4258   0.01499   0.00708  -0.1321   0.0431   0.0507
   1.250   0.4475   0.01457   0.00653  -0.1306   0.0421   0.0512
   1.500   0.4688   0.01422   0.00606  -0.1289   0.0413   0.0518
   1.750   0.4902   0.01399   0.00574  -0.1273   0.0406   0.0522
   2.000   0.5120   0.01390   0.00557  -0.1257   0.0402   0.0525
   2.250   0.5334   0.01381   0.00542  -0.1241   0.0395   0.0528
   2.500   0.5545   0.01369   0.00528  -0.1224   0.0390   0.0531
   2.750   0.5758   0.01368   0.00525  -0.1207   0.0387   0.0534
   3.000   0.5974   0.01369   0.00525  -0.1191   0.0385   0.0536
   3.250   0.6190   0.01371   0.00525  -0.1175   0.0383   0.0538
   3.500   0.6406   0.01376   0.00530  -0.1158   0.0380   0.0541
   3.750   0.6621   0.01382   0.00534  -0.1142   0.0379   0.0544
   4.000   0.6834   0.01388   0.00539  -0.1125   0.0375   0.0547
   4.250   0.7045   0.01397   0.00547  -0.1108   0.0373   0.0550
   4.500   0.7255   0.01407   0.00556  -0.1091   0.0371   0.0554
   4.750   0.7464   0.01418   0.00566  -0.1074   0.0368   0.0556
   5.000   0.7671   0.01431   0.00579  -0.1056   0.0366   0.0560
   5.250   0.7876   0.01445   0.00592  -0.1038   0.0362   0.0564
   5.500   0.8078   0.01461   0.00608  -0.1020   0.0359   0.0567
   5.750   0.8279   0.01477   0.00623  -0.1001   0.0357   0.0569
   6.000   0.8477   0.01497   0.00642  -0.0983   0.0355   0.0571
   6.250   0.8672   0.01516   0.00661  -0.0963   0.0352   0.0572
   6.500   0.8855   0.01537   0.00683  -0.0942   0.0349   0.0576
   6.750   0.9038   0.01560   0.00708  -0.0921   0.0348   0.0578
   7.000   0.9214   0.01591   0.00740  -0.0899   0.0346   0.0581
   7.250   0.9374   0.01632   0.00783  -0.0874   0.0343   0.0584
   7.500   0.9548   0.01665   0.00818  -0.0852   0.0342   0.0586
   7.750   0.9733   0.01694   0.00849  -0.0833   0.0341   0.0591
   8.000   0.9913   0.01728   0.00885  -0.0812   0.0340   0.0594
   8.250   1.0093   0.01761   0.00921  -0.0792   0.0339   0.0598
   8.500   1.0269   0.01796   0.00959  -0.0771   0.0338   0.0604
   8.750   1.0445   0.01834   0.00998  -0.0750   0.0336   0.0608
   9.000   1.0625   0.01871   0.01037  -0.0731   0.0335   0.0612
   9.250   1.0804   0.01908   0.01077  -0.0711   0.0333   0.0617
   9.500   1.0976   0.01950   0.01121  -0.0691   0.0331   0.0619
   9.750   1.1148   0.01993   0.01167  -0.0671   0.0329   0.0625
  10.000   1.1321   0.02038   0.01215  -0.0651   0.0327   0.0633
  10.250   1.1490   0.02085   0.01266  -0.0631   0.0325   0.0643
  10.500   1.1653   0.02139   0.01323  -0.0611   0.0325   0.0649
  10.750   1.1827   0.02186   0.01372  -0.0592   0.0322   0.0660
  11.000   1.1997   0.02238   0.01427  -0.0573   0.0321   0.0674
  11.250   1.2164   0.02291   0.01484  -0.0554   0.0319   0.0698
  11.500   1.2328   0.02347   0.01543  -0.0535   0.0317   0.0727
  11.750   1.2492   0.02407   0.01607  -0.0516   0.0317   0.0789
  12.000   1.2626   0.02415   0.01689  -0.0493   0.0315   0.5921
  12.250   1.3338   0.02466   0.01818  -0.0591   0.0312   1.0000
  12.500   1.3502   0.02532   0.01885  -0.0573   0.0311   1.0000
  12.750   1.3662   0.02599   0.01953  -0.0555   0.0309   1.0000
  13.000   1.3818   0.02669   0.02025  -0.0537   0.0308   1.0000
  13.250   1.3971   0.02744   0.02101  -0.0519   0.0307   1.0000
  13.500   1.4122   0.02822   0.02180  -0.0501   0.0306   1.0000
  13.750   1.4267   0.02908   0.02268  -0.0482   0.0304   1.0000
  14.000   1.4405   0.03003   0.02365  -0.0463   0.0302   1.0000
  14.250   1.4543   0.03102   0.02468  -0.0444   0.0300   1.0000
  14.500   1.4685   0.03182   0.02553  -0.0426   0.0299   1.0000
  14.750   1.4821   0.03270   0.02646  -0.0408   0.0298   1.0000
  15.000   1.4952   0.03358   0.02739  -0.0390   0.0297   1.0000
  15.250   1.5081   0.03455   0.02841  -0.0372   0.0296   1.0000
  15.500   1.5204   0.03553   0.02945  -0.0354   0.0295   1.0000
  15.750   1.5320   0.03658   0.03055  -0.0336   0.0294   1.0000
  16.000   1.5433   0.03770   0.03173  -0.0318   0.0293   1.0000
  16.250   1.5543   0.03885   0.03294  -0.0301   0.0292   1.0000
  16.500   1.5640   0.04010   0.03427  -0.0283   0.0290   1.0000
  16.750   1.5736   0.04137   0.03561  -0.0265   0.0289   1.0000
  17.000   1.5824   0.04272   0.03704  -0.0248   0.0288   1.0000
  17.250   1.5903   0.04418   0.03857  -0.0230   0.0286   1.0000
  17.500   1.5981   0.04562   0.04009  -0.0214   0.0285   1.0000
  17.750   1.6043   0.04729   0.04184  -0.0197   0.0284   1.0000
  18.000   1.6107   0.04890   0.04353  -0.0182   0.0282   1.0000
  18.250   1.6156   0.05069   0.04541  -0.0167   0.0281   1.0000
  18.500   1.6203   0.05256   0.04736  -0.0153   0.0280   1.0000
  18.750   1.6242   0.05451   0.04939  -0.0140   0.0279   1.0000
  19.000   1.6282   0.05649   0.05145  -0.0128   0.0277   1.0000
  19.250   1.6314   0.05857   0.05360  -0.0118   0.0276   1.0000
  19.500   1.6345   0.06073   0.05583  -0.0108   0.0275   1.0000
  19.750   1.6355   0.06318   0.05838  -0.0100   0.0274   1.0000
  20.000   1.6368   0.06566   0.06094  -0.0093   0.0273   1.0000
  20.250   1.6366   0.06837   0.06374  -0.0087   0.0273   1.0000
  20.500   1.6366   0.07114   0.06659  -0.0084   0.0272   1.0000
  20.750   1.6360   0.07402   0.06955  -0.0082   0.0271   1.0000
  21.000   1.6333   0.07724   0.07286  -0.0081   0.0270   1.0000
  21.250   1.6315   0.08045   0.07615  -0.0083   0.0270   1.0000
  21.500   1.6264   0.08419   0.08000  -0.0087   0.0269   1.0000
  21.750   1.6222   0.08790   0.08380  -0.0094   0.0269   1.0000
  22.000   1.6169   0.09187   0.08786  -0.0103   0.0268   1.0000
  22.250   1.6106   0.09606   0.09215  -0.0115   0.0267   1.0000
  22.500   1.6026   0.10063   0.09683  -0.0130   0.0267   1.0000
  22.750   1.5925   0.10568   0.10199  -0.0150   0.0266   1.0000
  23.000   1.5830   0.11078   0.10719  -0.0173   0.0266   1.0000
  23.250   1.5703   0.11658   0.11311  -0.0202   0.0265   1.0000
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