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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 100,000
Max Cl/Cd: 40.73 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1408-il-100000-n5.txt
Download as CSV file: xf-naca1408-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6355   0.09008   0.08516  -0.0065   1.0000   0.0274
  -9.250  -0.6419   0.08371   0.07884  -0.0108   1.0000   0.0273
  -9.000  -0.6502   0.07643   0.07162  -0.0169   1.0000   0.0271
  -8.750  -0.6621   0.06806   0.06322  -0.0243   1.0000   0.0266
  -8.500  -0.6726   0.06059   0.05557  -0.0286   1.0000   0.0264
  -8.250  -0.6795   0.05385   0.04853  -0.0310   1.0000   0.0264
  -8.000  -0.6814   0.04769   0.04192  -0.0319   1.0000   0.0266
  -7.750  -0.6778   0.04217   0.03583  -0.0318   1.0000   0.0271
  -7.500  -0.6686   0.03742   0.03042  -0.0311   1.0000   0.0279
  -7.250  -0.6545   0.03384   0.02615  -0.0301   1.0000   0.0296
  -7.000  -0.6368   0.03174   0.02394  -0.0295   1.0000   0.0318
  -6.750  -0.6173   0.02963   0.02146  -0.0286   1.0000   0.0339
  -6.500  -0.5965   0.02741   0.01883  -0.0276   1.0000   0.0365
  -6.250  -0.5746   0.02559   0.01657  -0.0266   1.0000   0.0401
  -6.000  -0.5531   0.02397   0.01489  -0.0259   1.0000   0.0434
  -5.750  -0.5302   0.02279   0.01352  -0.0251   1.0000   0.0478
  -5.500  -0.5071   0.02157   0.01206  -0.0241   1.0000   0.0523
  -5.250  -0.4848   0.02044   0.01090  -0.0233   1.0000   0.0565
  -5.000  -0.4616   0.01966   0.00998  -0.0225   1.0000   0.0626
  -4.750  -0.4390   0.01866   0.00892  -0.0215   1.0000   0.0665
  -4.500  -0.4164   0.01786   0.00810  -0.0206   1.0000   0.0712
  -4.250  -0.3931   0.01724   0.00737  -0.0197   1.0000   0.0783
  -4.000  -0.3703   0.01654   0.00669  -0.0189   1.0000   0.0891
  -3.750  -0.3472   0.01585   0.00603  -0.0181   1.0000   0.1033
  -3.500  -0.3240   0.01517   0.00549  -0.0174   1.0000   0.1308
  -3.250  -0.3007   0.01456   0.00507  -0.0168   1.0000   0.1783
  -3.000  -0.2774   0.01400   0.00474  -0.0162   1.0000   0.2397
  -2.750  -0.2543   0.01339   0.00452  -0.0157   1.0000   0.3286
  -2.500  -0.2323   0.01261   0.00440  -0.0148   1.0000   0.4696
  -2.250  -0.2113   0.01198   0.00436  -0.0133   1.0000   0.6117
  -2.000  -0.1902   0.01161   0.00436  -0.0113   1.0000   0.7201
  -1.750  -0.1674   0.01141   0.00443  -0.0092   1.0000   0.8272
  -1.500  -0.1264   0.01138   0.00443  -0.0111   1.0000   0.9320
  -1.250  -0.0743   0.01137   0.00430  -0.0162   1.0000   1.0000
  -1.000  -0.0574   0.01141   0.00423  -0.0146   1.0000   1.0000
  -0.750  -0.0301   0.01148   0.00418  -0.0150   0.9965   1.0000
  -0.500   0.0124   0.01155   0.00416  -0.0184   0.9870   1.0000
  -0.250   0.0545   0.01160   0.00413  -0.0217   0.9767   1.0000
   0.000   0.0961   0.01162   0.00411  -0.0247   0.9656   1.0000
   0.250   0.1360   0.01164   0.00410  -0.0273   0.9531   1.0000
   0.500   0.1739   0.01163   0.00409  -0.0294   0.9389   1.0000
   0.750   0.2108   0.01162   0.00408  -0.0312   0.9234   1.0000
   1.000   0.2453   0.01160   0.00408  -0.0324   0.9054   1.0000
   1.250   0.2775   0.01159   0.00408  -0.0329   0.8843   1.0000
   1.500   0.3090   0.01157   0.00408  -0.0333   0.8619   1.0000
   1.750   0.3386   0.01158   0.00409  -0.0332   0.8370   1.0000
   2.000   0.3664   0.01161   0.00412  -0.0326   0.8093   1.0000
   2.250   0.3933   0.01167   0.00416  -0.0319   0.7791   1.0000
   2.500   0.4191   0.01177   0.00424  -0.0309   0.7448   1.0000
   2.750   0.4445   0.01192   0.00432  -0.0299   0.7081   1.0000
   3.000   0.4691   0.01212   0.00443  -0.0287   0.6677   1.0000
   3.250   0.4931   0.01238   0.00458  -0.0275   0.6219   1.0000
   3.500   0.5161   0.01272   0.00473  -0.0261   0.5658   1.0000
   3.750   0.5377   0.01320   0.00489  -0.0246   0.4900   1.0000
   4.000   0.5584   0.01385   0.00510  -0.0232   0.3967   1.0000
   4.250   0.5799   0.01458   0.00546  -0.0221   0.3073   1.0000
   4.500   0.6015   0.01543   0.00592  -0.0213   0.2240   1.0000
   4.750   0.6230   0.01640   0.00654  -0.0205   0.1503   1.0000
   5.000   0.6449   0.01740   0.00730  -0.0197   0.1052   1.0000
   5.250   0.6670   0.01836   0.00819  -0.0188   0.0861   1.0000
   5.500   0.6898   0.01921   0.00911  -0.0179   0.0765   1.0000
   5.750   0.7118   0.02013   0.01006  -0.0171   0.0688   1.0000
   6.000   0.7344   0.02098   0.01101  -0.0162   0.0626   1.0000
   6.250   0.7551   0.02222   0.01224  -0.0152   0.0585   1.0000
   6.500   0.7783   0.02315   0.01339  -0.0144   0.0534   1.0000
   6.750   0.8005   0.02425   0.01456  -0.0136   0.0487   1.0000
   7.000   0.8218   0.02582   0.01618  -0.0127   0.0446   1.0000
   7.250   0.8445   0.02713   0.01774  -0.0118   0.0401   1.0000
   7.500   0.8660   0.02868   0.01941  -0.0110   0.0369   1.0000
   7.750   0.8861   0.03076   0.02165  -0.0102   0.0337   1.0000
   8.000   0.9065   0.03289   0.02424  -0.0090   0.0311   1.0000
   8.250   0.9248   0.03534   0.02707  -0.0079   0.0291   1.0000
   8.500   0.9414   0.03731   0.02929  -0.0068   0.0270   1.0000
   8.750   0.9550   0.03986   0.03195  -0.0059   0.0253   1.0000
   9.000   0.9644   0.04316   0.03582  -0.0042   0.0243   1.0000
   9.250   0.9684   0.04713   0.04036  -0.0024   0.0236   1.0000
   9.500   0.9667   0.05147   0.04521  -0.0007   0.0232   1.0000
   9.750   0.9590   0.05600   0.05016   0.0009   0.0229   1.0000
  10.000   0.9454   0.06048   0.05498   0.0021   0.0228   1.0000
  10.250   0.9263   0.06488   0.05962   0.0029   0.0229   1.0000
  10.500   0.9056   0.07017   0.06509   0.0011   0.0230   1.0000
  10.750   0.8841   0.07693   0.07201  -0.0036   0.0232   1.0000
  11.000   0.8627   0.08573   0.08092  -0.0109   0.0236   1.0000
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