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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 58.34 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-1000000-n5.txt
Download as CSV file: xf-cp-100-050-gn-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.1618   0.14752   0.14531  -0.1076   0.9743   0.0159
 -13.750  -0.1508   0.14453   0.14232  -0.1098   0.9737   0.0165
 -13.500  -0.1470   0.13937   0.13714  -0.1124   0.9730   0.0173
 -13.250  -0.1329   0.13710   0.13487  -0.1147   0.9724   0.0175
 -13.000  -0.1206   0.13420   0.13196  -0.1171   0.9719   0.0175
 -12.750  -0.1121   0.13249   0.13025  -0.1176   0.9689   0.0177
 -12.500  -0.1025   0.13005   0.12781  -0.1190   0.9667   0.0178
 -12.250  -0.0909   0.12771   0.12547  -0.1207   0.9649   0.0182
 -12.000  -0.0791   0.12499   0.12274  -0.1228   0.9635   0.0186
 -10.000   0.0214   0.10289   0.10056  -0.1411   0.9484   0.0213
  -9.500   0.0472   0.09498   0.09259  -0.1488   0.9445   0.0226
  -9.250   0.0598   0.09329   0.09090  -0.1498   0.9406   0.0227
  -9.000   0.0750   0.09121   0.08882  -0.1519   0.9371   0.0229
  -8.750   0.0932   0.08891   0.08650  -0.1549   0.9342   0.0230
  -8.500   0.1148   0.08669   0.08426  -0.1585   0.9319   0.0234
  -8.250   0.1364   0.08408   0.08162  -0.1626   0.9295   0.0238
  -8.000   0.1477   0.08179   0.07933  -0.1641   0.9248   0.0240
  -7.500   0.1741   0.07535   0.07281  -0.1705   0.9152   0.0256
  -7.250   0.1892   0.07330   0.07074  -0.1725   0.9110   0.0256
  -7.000   0.2011   0.07160   0.06904  -0.1734   0.9056   0.0257
  -6.750   0.2186   0.07032   0.06774  -0.1748   0.9009   0.0261
  -6.500   0.2341   0.06834   0.06573  -0.1768   0.8962   0.0263
  -6.250   0.2434   0.06685   0.06425  -0.1768   0.8907   0.0267
  -6.000   0.2527   0.06493   0.06231  -0.1775   0.8845   0.0270
  -5.750   0.2606   0.06292   0.06027  -0.1781   0.8786   0.0276
  -5.500   0.2539   0.06011   0.05745  -0.1775   0.8706   0.0285
  -5.250   0.2677   0.05883   0.05615  -0.1782   0.8655   0.0287
  -5.000   0.2813   0.05755   0.05486  -0.1788   0.8607   0.0288
  -4.750   0.2931   0.05605   0.05336  -0.1793   0.8554   0.0290
  -4.500   0.3076   0.05475   0.05205  -0.1800   0.8503   0.0294
  -4.250   0.3226   0.05315   0.05042  -0.1812   0.8454   0.0298
  -4.000   0.3357   0.05133   0.04860  -0.1821   0.8400   0.0301
  -3.500   0.3637   0.04558   0.04273  -0.1872   0.8263   0.0317
  -3.250   0.3809   0.04443   0.04156  -0.1875   0.8172   0.0319
  -3.000   0.3996   0.04338   0.04046  -0.1880   0.8099   0.0321
  -2.750   0.4183   0.04210   0.03917  -0.1886   0.8011   0.0323
  -2.500   0.4380   0.04065   0.03767  -0.1895   0.7939   0.0327
  -2.250   0.4577   0.03902   0.03598  -0.1906   0.7832   0.0330
  -1.750   0.5058   0.03340   0.03017  -0.1962   0.7651   0.0350
  -1.500   0.5261   0.03248   0.02919  -0.1960   0.7544   0.0352
  -1.250   0.5443   0.03168   0.02831  -0.1952   0.7392   0.0354
  -1.000   0.5637   0.03075   0.02731  -0.1947   0.7242   0.0357
  -0.750   0.5786   0.02971   0.02612  -0.1933   0.6984   0.0359
  -0.500   0.5938   0.02866   0.02494  -0.1918   0.6738   0.0363
  -0.250   0.6030   0.02766   0.02374  -0.1888   0.6411   0.0367
   0.250   0.6215   0.02405   0.01954  -0.1834   0.5548   0.0386
   0.500   0.5971   0.02505   0.01981  -0.1731   0.3966   0.0387
   0.750   0.5741   0.02643   0.02032  -0.1636   0.1658   0.0387
   1.000   0.5829   0.02645   0.01996  -0.1604   0.0424   0.0388
   1.250   0.6056   0.02586   0.01931  -0.1598   0.0371   0.0391
   1.500   0.6297   0.02500   0.01836  -0.1596   0.0345   0.0395
   1.750   0.6557   0.02380   0.01705  -0.1596   0.0332   0.0400
   2.000   0.6956   0.01905   0.01177  -0.1626   0.0328   0.0425
   2.250   0.7181   0.01872   0.01136  -0.1615   0.0320   0.0428
   2.500   0.7411   0.01806   0.01056  -0.1606   0.0312   0.0432
   2.750   0.7659   0.01592   0.00786  -0.1599   0.0307   0.0455
   3.000   0.7871   0.01574   0.00754  -0.1584   0.0302   0.0458
   3.250   0.8080   0.01557   0.00727  -0.1570   0.0297   0.0461
   3.500   0.8282   0.01563   0.00730  -0.1553   0.0293   0.0464
   3.750   0.8477   0.01575   0.00739  -0.1535   0.0288   0.0466
   4.000   0.8679   0.01589   0.00752  -0.1519   0.0286   0.0469
   4.250   0.8879   0.01601   0.00762  -0.1502   0.0284   0.0472
   4.500   0.9078   0.01614   0.00772  -0.1485   0.0283   0.0474
   4.750   0.9270   0.01632   0.00789  -0.1467   0.0281   0.0477
   5.000   0.9460   0.01650   0.00805  -0.1448   0.0279   0.0481
   5.250   0.9647   0.01674   0.00828  -0.1429   0.0278   0.0487
   5.500   0.9834   0.01697   0.00850  -0.1411   0.0276   0.0489
   5.750   1.0020   0.01721   0.00872  -0.1392   0.0274   0.0492
   6.000   1.0198   0.01748   0.00900  -0.1372   0.0273   0.0494
   6.250   1.0373   0.01780   0.00932  -0.1352   0.0271   0.0497
   6.500   1.0549   0.01813   0.00966  -0.1332   0.0270   0.0498
   6.750   1.0726   0.01847   0.01000  -0.1313   0.0268   0.0500
   7.000   1.0891   0.01887   0.01041  -0.1291   0.0266   0.0501
   7.250   1.1055   0.01924   0.01080  -0.1270   0.0265   0.0504
   7.500   1.1224   0.01963   0.01120  -0.1250   0.0262   0.0507
   7.750   1.1393   0.02005   0.01164  -0.1231   0.0260   0.0511
   8.000   1.1553   0.02054   0.01215  -0.1210   0.0258   0.0517
   8.250   1.1704   0.02107   0.01271  -0.1188   0.0256   0.0520
   8.500   1.1857   0.02162   0.01327  -0.1166   0.0255   0.0524
   8.750   1.2002   0.02224   0.01391  -0.1144   0.0253   0.0527
   9.000   1.2134   0.02294   0.01465  -0.1121   0.0251   0.0534
   9.250   1.2257   0.02374   0.01547  -0.1096   0.0249   0.0537
   9.500   1.2367   0.02465   0.01643  -0.1071   0.0247   0.0539
   9.750   1.2511   0.02535   0.01715  -0.1050   0.0247   0.0542
  10.000   1.2662   0.02602   0.01786  -0.1031   0.0246   0.0548
  10.250   1.2816   0.02668   0.01854  -0.1012   0.0245   0.0553
  10.500   1.2952   0.02748   0.01939  -0.0992   0.0244   0.0563
  10.750   1.3101   0.02821   0.02015  -0.0973   0.0243   0.0573
  11.000   1.3240   0.02904   0.02102  -0.0954   0.0242   0.0585
  11.250   1.3385   0.02984   0.02186  -0.0936   0.0241   0.0605
  11.500   1.3526   0.03068   0.02274  -0.0917   0.0239   0.0638
  11.750   1.3666   0.03155   0.02366  -0.0899   0.0238   0.0697
  12.000   1.3803   0.03216   0.02480  -0.0881   0.0237   0.4667
  12.500   1.4480   0.03402   0.02753  -0.0932   0.0233   1.0000
  12.750   1.4615   0.03496   0.02850  -0.0915   0.0231   1.0000
  13.000   1.4750   0.03591   0.02947  -0.0897   0.0229   1.0000
  13.250   1.4879   0.03691   0.03050  -0.0879   0.0228   1.0000
  13.500   1.5012   0.03789   0.03151  -0.0861   0.0226   1.0000
  13.750   1.5137   0.03892   0.03257  -0.0844   0.0225   1.0000
  14.000   1.5259   0.04001   0.03369  -0.0826   0.0224   1.0000
  14.250   1.5384   0.04107   0.03479  -0.0809   0.0223   1.0000
  14.500   1.5506   0.04217   0.03592  -0.0792   0.0222   1.0000
  14.750   1.5622   0.04334   0.03713  -0.0776   0.0221   1.0000
  15.000   1.5736   0.04453   0.03835  -0.0759   0.0220   1.0000
  15.250   1.5850   0.04571   0.03957  -0.0743   0.0219   1.0000
  15.500   1.5955   0.04698   0.04088  -0.0727   0.0217   1.0000
  15.750   1.6058   0.04832   0.04226  -0.0711   0.0217   1.0000
  16.000   1.6160   0.04966   0.04364  -0.0696   0.0216   1.0000
  16.250   1.6258   0.05106   0.04509  -0.0680   0.0215   1.0000
  16.500   1.6349   0.05256   0.04663  -0.0665   0.0214   1.0000
  16.750   1.6437   0.05410   0.04822  -0.0650   0.0213   1.0000
  17.000   1.6522   0.05571   0.04989  -0.0635   0.0212   1.0000
  17.250   1.6594   0.05759   0.05186  -0.0619   0.0209   1.0000
  17.500   1.6664   0.05938   0.05374  -0.0605   0.0209   1.0000
  17.750   1.6732   0.06121   0.05565  -0.0592   0.0209   1.0000
  18.000   1.6790   0.06317   0.05770  -0.0580   0.0208   1.0000
  18.250   1.6843   0.06519   0.05981  -0.0568   0.0207   1.0000
  18.500   1.6890   0.06731   0.06203  -0.0557   0.0206   1.0000
  18.750   1.6927   0.06958   0.06440  -0.0547   0.0205   1.0000
  19.000   1.6959   0.07198   0.06691  -0.0537   0.0204   1.0000
  19.250   1.6977   0.07460   0.06964  -0.0529   0.0203   1.0000
  19.500   1.6986   0.07738   0.07254  -0.0521   0.0202   1.0000
  19.750   1.6984   0.08033   0.07561  -0.0515   0.0201   1.0000
  20.000   1.6961   0.08363   0.07905  -0.0511   0.0200   1.0000
  20.250   1.6932   0.08707   0.08262  -0.0508   0.0199   1.0000
  20.500   1.6892   0.09070   0.08639  -0.0508   0.0197   1.0000
  20.750   1.6823   0.09487   0.09072  -0.0510   0.0196   1.0000
  21.000   1.6753   0.09912   0.09511  -0.0515   0.0195   1.0000
  21.250   1.6665   0.10371   0.09986  -0.0524   0.0194   1.0000
  21.500   1.6556   0.10873   0.10504  -0.0536   0.0193   1.0000
  21.750   1.6442   0.11398   0.11044  -0.0553   0.0191   1.0000
  22.000   1.6285   0.12011   0.11674  -0.0576   0.0191   1.0000
  22.250   1.6119   0.12657   0.12338  -0.0605   0.0190   1.0000
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