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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=9


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: 50.72 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-1000000.txt
Download as CSV file: xf-cp-080-050-gn-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0603   0.10778   0.10578  -0.0956   0.9757   0.0358
  -9.250  -0.0505   0.10453   0.10252  -0.0975   0.9748   0.0368
  -9.000  -0.0533   0.09919   0.09716  -0.1013   0.9739   0.0374
  -8.750  -0.0381   0.09626   0.09424  -0.1025   0.9733   0.0375
  -8.500  -0.0239   0.09351   0.09149  -0.1041   0.9726   0.0377
  -8.250  -0.0092   0.09088   0.08886  -0.1059   0.9720   0.0379
  -8.000   0.0056   0.08805   0.08604  -0.1080   0.9713   0.0382
  -7.750   0.0193   0.08526   0.08325  -0.1100   0.9707   0.0387
  -7.500   0.0314   0.08239   0.08038  -0.1117   0.9685   0.0392
  -7.250   0.0342   0.07848   0.07646  -0.1142   0.9646   0.0408
  -7.000   0.0419   0.07372   0.07168  -0.1183   0.9616   0.0410
  -6.750   0.0565   0.07103   0.06900  -0.1195   0.9612   0.0411
  -6.500   0.0795   0.06800   0.06596  -0.1226   0.9588   0.0413
  -6.250   0.1001   0.06516   0.06311  -0.1256   0.9572   0.0415
  -6.000   0.1135   0.06276   0.06071  -0.1270   0.9525   0.0418
  -5.750   0.1285   0.06031   0.05826  -0.1289   0.9471   0.0423
  -5.500   0.1496   0.05721   0.05513  -0.1327   0.9427   0.0431
  -5.250   0.1337   0.05275   0.05062  -0.1379   0.9311   0.0446
  -5.000   0.1534   0.04978   0.04763  -0.1387   0.9270   0.0448
  -4.750   0.1627   0.04796   0.04581  -0.1376   0.9181   0.0449
  -4.500   0.1749   0.04597   0.04380  -0.1381   0.9111   0.0450
  -4.250   0.1800   0.04442   0.04224  -0.1370   0.9030   0.0452
  -4.000   0.1860   0.04271   0.04050  -0.1367   0.8937   0.0454
  -3.750   0.1942   0.04106   0.03885  -0.1367   0.8859   0.0458
  -3.500   0.2033   0.03913   0.03689  -0.1372   0.8774   0.0462
  -3.250   0.2124   0.03716   0.03489  -0.1378   0.8678   0.0469
  -3.000   0.2164   0.03120   0.02879  -0.1466   0.8615   0.0486
  -2.750   0.2304   0.02939   0.02694  -0.1460   0.8534   0.0488
  -2.500   0.2451   0.02787   0.02541  -0.1454   0.8438   0.0489
  -2.250   0.2614   0.02640   0.02390  -0.1452   0.8347   0.0490
  -2.000   0.2780   0.02500   0.02247  -0.1450   0.8244   0.0493
  -1.750   0.2946   0.02364   0.02105  -0.1449   0.8093   0.0496
  -1.500   0.3114   0.02226   0.01958  -0.1449   0.7912   0.0501
  -1.250   0.3274   0.02093   0.01811  -0.1446   0.7649   0.0511
  -1.000   0.3754   0.03047   0.02722  -0.1611   0.7744   0.0529
  -0.750   0.3800   0.03005   0.02648  -0.1568   0.7073   0.0531
  -0.500   0.3698   0.03055   0.02630  -0.1492   0.5584   0.0532
  -0.250   0.3450   0.03230   0.02675  -0.1393   0.2292   0.0532
   0.000   0.3501   0.03242   0.02634  -0.1354   0.0587   0.0533
   0.250   0.3698   0.03162   0.02549  -0.1344   0.0545   0.0536
   0.500   0.3902   0.03078   0.02462  -0.1334   0.0528   0.0540
   0.750   0.4111   0.02978   0.02356  -0.1325   0.0512   0.0547
   1.000   0.4382   0.02538   0.01878  -0.1328   0.0506   0.0576
   1.250   0.4572   0.02486   0.01825  -0.1312   0.0494   0.0578
   1.500   0.4762   0.02435   0.01772  -0.1296   0.0490   0.0581
   1.750   0.4948   0.02386   0.01720  -0.1278   0.0484   0.0585
   2.000   0.5138   0.02332   0.01662  -0.1260   0.0480   0.0591
   2.250   0.5337   0.02255   0.01576  -0.1243   0.0475   0.0604
   2.500   0.5554   0.02013   0.01301  -0.1225   0.0472   0.0629
   2.750   0.5747   0.01985   0.01271  -0.1207   0.0467   0.0632
   3.000   0.5944   0.01958   0.01241  -0.1190   0.0463   0.0637
   3.250   0.6143   0.01927   0.01205  -0.1172   0.0459   0.0644
   3.500   0.6356   0.01817   0.01064  -0.1152   0.0454   0.0682
   3.750   0.6549   0.01801   0.01047  -0.1134   0.0451   0.0686
   4.000   0.6727   0.01800   0.01044  -0.1112   0.0444   0.0690
   4.250   0.6888   0.01812   0.01054  -0.1087   0.0439   0.0697
   4.500   0.7082   0.01806   0.01044  -0.1067   0.0437   0.0711
   4.750   0.7291   0.01778   0.00994  -0.1048   0.0435   0.0742
   5.000   0.7483   0.01775   0.00993  -0.1029   0.0433   0.0748
   5.250   0.7675   0.01782   0.00999  -0.1010   0.0431   0.0755
   5.500   0.7864   0.01794   0.01010  -0.0989   0.0429   0.0767
   5.750   0.8053   0.01807   0.01012  -0.0968   0.0427   0.0810
   6.000   0.8237   0.01817   0.01024  -0.0948   0.0425   0.0818
   6.250   0.8423   0.01835   0.01042  -0.0928   0.0422   0.0830
   6.500   0.8608   0.01859   0.01063  -0.0907   0.0420   0.0845
   6.750   0.8798   0.01879   0.01080  -0.0888   0.0418   0.0890
   7.000   0.8985   0.01901   0.01103  -0.0868   0.0415   0.0900
   7.250   0.9187   0.01844   0.01019  -0.0843   0.0412   0.0676
   7.500   0.9377   0.01863   0.01038  -0.0824   0.0409   0.0679
   7.750   0.9568   0.01892   0.01069  -0.0805   0.0406   0.0683
   8.000   0.9764   0.01929   0.01107  -0.0788   0.0404   0.0685
   8.250   0.9961   0.01964   0.01143  -0.0771   0.0401   0.0688
   8.500   1.0164   0.02005   0.01184  -0.0755   0.0398   0.0692
   8.750   1.0380   0.02053   0.01232  -0.0741   0.0396   0.0696
   9.000   1.0644   0.02123   0.01301  -0.0737   0.0392   0.0704
   9.250   1.1100   0.02253   0.01428  -0.0767   0.0388   0.0717
   9.500   1.1285   0.02285   0.01465  -0.0747   0.0387   0.0721
   9.750   1.1475   0.02320   0.01507  -0.0728   0.0385   0.0728
  10.000   1.1702   0.02370   0.01561  -0.0717   0.0383   0.0737
  10.250   1.1947   0.02428   0.01625  -0.0708   0.0381   0.0754
  10.500   1.2181   0.02485   0.01687  -0.0698   0.0379   0.0767
  10.750   1.2406   0.02545   0.01753  -0.0686   0.0375   0.0789
  11.000   1.2638   0.02611   0.01825  -0.0676   0.0371   0.0831
  11.250   1.2872   0.02681   0.01905  -0.0667   0.0369   0.1059
  11.500   1.3464   0.02708   0.02083  -0.0736   0.0364   1.0000
  11.750   1.3670   0.02786   0.02163  -0.0723   0.0362   1.0000
  12.000   1.3864   0.02861   0.02241  -0.0707   0.0359   1.0000
  12.250   1.4053   0.02938   0.02321  -0.0691   0.0357   1.0000
  12.500   1.4246   0.03025   0.02411  -0.0676   0.0355   1.0000
  12.750   1.4425   0.03105   0.02493  -0.0659   0.0354   1.0000
  13.000   1.4579   0.03173   0.02562  -0.0639   0.0352   1.0000
  13.250   1.4746   0.03260   0.02652  -0.0621   0.0350   1.0000
  13.500   1.4926   0.03369   0.02764  -0.0606   0.0348   1.0000
  13.750   1.5129   0.03524   0.02924  -0.0596   0.0346   1.0000
  14.000   1.5236   0.03856   0.03283  -0.0577   0.0341   1.0000
  14.250   1.5241   0.03925   0.03365  -0.0535   0.0339   1.0000
  14.500   1.5258   0.04064   0.03521  -0.0498   0.0337   1.0000
  14.750   1.5270   0.04246   0.03721  -0.0463   0.0335   1.0000
  15.000   1.5242   0.04467   0.03964  -0.0426   0.0333   1.0000
  15.250   1.5186   0.04723   0.04242  -0.0388   0.0330   1.0000
  15.500   1.5072   0.05025   0.04567  -0.0348   0.0328   1.0000
  15.750   1.4946   0.05322   0.04886  -0.0310   0.0326   1.0000
  16.000   1.4774   0.05668   0.05254  -0.0274   0.0324   1.0000
  16.250   1.4553   0.06065   0.05674  -0.0239   0.0323   1.0000
  16.500   1.4184   0.06645   0.06283  -0.0207   0.0323   1.0000
  16.750   1.3822   0.07235   0.06900  -0.0186   0.0322   1.0000
  17.000   1.3552   0.07749   0.07432  -0.0177   0.0321   1.0000
  17.250   1.3080   0.08574   0.08283  -0.0183   0.0321   1.0000
  17.500   1.1996   0.10534   0.10291  -0.0267   0.0328   1.0000
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