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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=1


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: 64.23 at α=8.5°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-080-050-gn-1000000-n1.txt
Download as CSV file: xf-cp-080-050-gn-1000000-n1.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 =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.0642   0.09221   0.08944  -0.1277   0.8938   0.0233
  -8.750  -0.0530   0.08932   0.08651  -0.1301   0.8873   0.0237
  -8.500  -0.0441   0.08632   0.08348  -0.1323   0.8806   0.0245
  -8.000  -0.0211   0.08176   0.07886  -0.1356   0.8663   0.0250
  -7.750  -0.0102   0.07968   0.07674  -0.1368   0.8585   0.0252
  -7.500   0.0009   0.07775   0.07479  -0.1379   0.8522   0.0254
  -7.250   0.0088   0.07539   0.07240  -0.1390   0.8437   0.0260
  -7.000   0.0142   0.07344   0.07030  -0.1392   0.8145   0.0264
  -6.750   0.0240   0.07099   0.06794  -0.1407   0.8288   0.0267
  -6.500   0.0278   0.06885   0.06572  -0.1409   0.8091   0.0273
  -6.250   0.0337   0.06639   0.06330  -0.1420   0.8138   0.0278
  -6.000   0.0342   0.06529   0.06200  -0.1401   0.7678   0.0281
  -5.750   0.0391   0.06341   0.06014  -0.1402   0.7671   0.0283
  -1.750   0.1583   0.01527   0.00757  -0.1429   0.0363   0.0421
  -1.500   0.1805   0.01437   0.00647  -0.1419   0.0353   0.0427
  -1.250   0.2040   0.01389   0.00586  -0.1409   0.0346   0.0431
  -1.000   0.2279   0.01355   0.00542  -0.1399   0.0340   0.0434
  -0.750   0.2520   0.01331   0.00510  -0.1390   0.0334   0.0437
  -0.500   0.2760   0.01309   0.00481  -0.1379   0.0331   0.0440
  -0.250   0.3002   0.01295   0.00461  -0.1369   0.0328   0.0443
   0.000   0.3241   0.01278   0.00438  -0.1359   0.0325   0.0446
   0.250   0.3483   0.01275   0.00432  -0.1348   0.0323   0.0448
   0.500   0.3723   0.01271   0.00425  -0.1337   0.0321   0.0450
   0.750   0.3961   0.01266   0.00417  -0.1325   0.0318   0.0452
   1.000   0.4195   0.01265   0.00413  -0.1313   0.0315   0.0454
   1.250   0.4421   0.01260   0.00405  -0.1298   0.0313   0.0456
   1.500   0.4644   0.01259   0.00401  -0.1283   0.0311   0.0458
   1.750   0.4865   0.01256   0.00395  -0.1268   0.0307   0.0460
   2.000   0.5087   0.01255   0.00392  -0.1253   0.0304   0.0463
   2.250   0.5309   0.01256   0.00390  -0.1238   0.0301   0.0465
   2.500   0.5530   0.01258   0.00390  -0.1222   0.0300   0.0468
   2.750   0.5750   0.01260   0.00391  -0.1207   0.0299   0.0470
   3.000   0.5969   0.01265   0.00393  -0.1191   0.0299   0.0472
   3.250   0.6190   0.01270   0.00397  -0.1176   0.0298   0.0475
   3.500   0.6411   0.01277   0.00403  -0.1160   0.0297   0.0479
   3.750   0.6631   0.01285   0.00410  -0.1145   0.0297   0.0481
   4.000   0.6849   0.01295   0.00419  -0.1129   0.0296   0.0482
   4.250   0.7066   0.01306   0.00429  -0.1113   0.0295   0.0483
   4.500   0.7282   0.01318   0.00441  -0.1097   0.0294   0.0484
   4.750   0.7497   0.01330   0.00453  -0.1081   0.0293   0.0485
   5.000   0.7711   0.01344   0.00467  -0.1064   0.0293   0.0485
   5.250   0.7923   0.01359   0.00482  -0.1048   0.0292   0.0487
   5.500   0.8133   0.01374   0.00498  -0.1031   0.0290   0.0488
   5.750   0.8340   0.01391   0.00515  -0.1013   0.0290   0.0488
   6.000   0.8548   0.01409   0.00534  -0.0996   0.0289   0.0491
   6.250   0.8755   0.01426   0.00553  -0.0979   0.0288   0.0493
   6.500   0.8959   0.01446   0.00574  -0.0961   0.0286   0.0498
   6.750   0.9160   0.01466   0.00595  -0.0943   0.0285   0.0500
   7.000   0.9359   0.01488   0.00618  -0.0925   0.0283   0.0502
   7.250   0.9560   0.01509   0.00640  -0.0907   0.0281   0.0504
   7.500   0.9758   0.01533   0.00665  -0.0888   0.0279   0.0504
   7.750   0.9952   0.01557   0.00691  -0.0870   0.0277   0.0508
   8.000   1.0144   0.01584   0.00718  -0.0851   0.0276   0.0508
   8.250   1.0335   0.01611   0.00747  -0.0832   0.0275   0.0509
   8.500   1.0527   0.01639   0.00777  -0.0813   0.0273   0.0511
   8.750   1.0713   0.01669   0.00809  -0.0794   0.0272   0.0515
   9.000   1.0899   0.01700   0.00841  -0.0774   0.0270   0.0517
   9.250   1.1081   0.01733   0.00877  -0.0755   0.0270   0.0519
   9.500   1.1266   0.01766   0.00911  -0.0736   0.0268   0.0519
   9.750   1.1447   0.01801   0.00948  -0.0716   0.0267   0.0522
  10.000   1.1623   0.01838   0.00988  -0.0697   0.0266   0.0524
  10.250   1.1801   0.01876   0.01027  -0.0677   0.0265   0.0526
  10.500   1.1974   0.01917   0.01071  -0.0658   0.0265   0.0526
  10.750   1.2151   0.01957   0.01113  -0.0638   0.0263   0.0530
  11.000   1.2319   0.02000   0.01159  -0.0618   0.0262   0.0534
  11.250   1.2489   0.02045   0.01207  -0.0599   0.0261   0.0544
  11.500   1.2656   0.02093   0.01258  -0.0579   0.0260   0.0553
  11.750   1.2816   0.02143   0.01312  -0.0559   0.0259   0.0559
  12.000   1.2975   0.02196   0.01368  -0.0539   0.0258   0.0564
  12.250   1.3136   0.02249   0.01424  -0.0520   0.0257   0.0568
  12.500   1.3291   0.02307   0.01486  -0.0500   0.0256   0.0578
  12.750   1.3442   0.02366   0.01549  -0.0480   0.0255   0.0596
  13.000   1.3596   0.02426   0.01612  -0.0461   0.0254   0.0610
  13.250   1.3747   0.02488   0.01680  -0.0442   0.0253   0.0670
  13.500   1.3824   0.02476   0.01774  -0.0410   0.0252   0.8023
  14.250   1.4905   0.02740   0.02083  -0.0490   0.0249   1.0000
  14.500   1.5046   0.02820   0.02166  -0.0471   0.0247   1.0000
  14.750   1.5183   0.02904   0.02252  -0.0453   0.0245   1.0000
  15.000   1.5318   0.02989   0.02341  -0.0435   0.0245   1.0000
  15.250   1.5447   0.03080   0.02435  -0.0417   0.0244   1.0000
  15.500   1.5575   0.03173   0.02532  -0.0399   0.0242   1.0000
  15.750   1.5703   0.03267   0.02630  -0.0382   0.0241   1.0000
  16.000   1.5821   0.03370   0.02737  -0.0364   0.0241   1.0000
  16.250   1.5938   0.03474   0.02846  -0.0346   0.0240   1.0000
  16.500   1.6057   0.03578   0.02953  -0.0330   0.0238   1.0000
  16.750   1.6174   0.03685   0.03064  -0.0313   0.0237   1.0000
  17.000   1.6289   0.03796   0.03178  -0.0298   0.0235   1.0000
  17.250   1.6392   0.03918   0.03306  -0.0281   0.0235   1.0000
  17.500   1.6511   0.04028   0.03418  -0.0267   0.0232   1.0000
  17.750   1.6607   0.04158   0.03554  -0.0251   0.0232   1.0000
  18.000   1.6711   0.04283   0.03682  -0.0237   0.0230   1.0000
  18.250   1.6807   0.04417   0.03820  -0.0223   0.0229   1.0000
  18.500   1.6898   0.04558   0.03966  -0.0209   0.0229   1.0000
  18.750   1.6985   0.04704   0.04117  -0.0195   0.0228   1.0000
  19.000   1.7064   0.04859   0.04278  -0.0182   0.0227   1.0000
  19.250   1.7127   0.05033   0.04459  -0.0169   0.0226   1.0000
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