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NACA 1412 (naca1412-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 1412 (naca1412-il)
Reynolds number: 50,000
Max Cl/Cd: 29.62 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca1412-il-50000.txt
Download as CSV file: xf-naca1412-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1412                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4999   0.10753   0.09979   0.0051   1.0000   0.3523
  -9.000  -0.6909   0.07418   0.06661  -0.0317   1.0000   0.1742
  -8.750  -0.6907   0.06927   0.06166  -0.0318   1.0000   0.1732
  -8.500  -0.6975   0.06418   0.05644  -0.0317   1.0000   0.1721
  -8.250  -0.7049   0.05918   0.05122  -0.0312   1.0000   0.1713
  -8.000  -0.7098   0.05444   0.04619  -0.0302   1.0000   0.1708
  -7.750  -0.7107   0.05007   0.04144  -0.0288   1.0000   0.1707
  -7.500  -0.7078   0.04611   0.03703  -0.0271   1.0000   0.1715
  -7.250  -0.7024   0.04262   0.03295  -0.0251   1.0000   0.1738
  -7.000  -0.6838   0.04055   0.03098  -0.0238   1.0000   0.1800
  -6.750  -0.6704   0.03806   0.02813  -0.0221   1.0000   0.1863
  -6.500  -0.6548   0.03551   0.02524  -0.0206   1.0000   0.1923
  -6.250  -0.6361   0.03366   0.02326  -0.0191   1.0000   0.2018
  -6.000  -0.6172   0.03198   0.02150  -0.0177   1.0000   0.2144
  -5.750  -0.5978   0.03032   0.01975  -0.0162   1.0000   0.2293
  -5.500  -0.5785   0.02889   0.01825  -0.0147   1.0000   0.2494
  -5.250  -0.5588   0.02757   0.01702  -0.0132   1.0000   0.2734
  -5.000  -0.5396   0.02640   0.01591  -0.0116   1.0000   0.3034
  -4.750  -0.5204   0.02537   0.01507  -0.0098   1.0000   0.3381
  -4.500  -0.5014   0.02442   0.01431  -0.0080   1.0000   0.3789
  -4.250  -0.4824   0.02354   0.01370  -0.0060   1.0000   0.4236
  -4.000  -0.4635   0.02277   0.01317  -0.0038   1.0000   0.4732
  -3.750  -0.4449   0.02212   0.01279  -0.0015   1.0000   0.5271
  -3.500  -0.4272   0.02162   0.01256   0.0013   1.0000   0.5829
  -3.250  -0.4103   0.02127   0.01247   0.0047   1.0000   0.6404
  -3.000  -0.3946   0.02104   0.01246   0.0085   1.0000   0.6995
  -2.750  -0.3794   0.02097   0.01257   0.0129   1.0000   0.7594
  -2.500  -0.3602   0.02114   0.01286   0.0170   1.0000   0.8207
  -2.250  -0.3153   0.02173   0.01336   0.0168   1.0000   0.8888
  -2.000  -0.1698   0.02270   0.01379  -0.0025   1.0000   0.9559
  -1.750  -0.0265   0.02209   0.01272  -0.0252   1.0000   1.0000
  -1.500  -0.0445   0.02156   0.01220  -0.0206   1.0000   1.0000
  -1.250  -0.0644   0.02118   0.01180  -0.0153   1.0000   1.0000
  -1.000  -0.0811   0.02094   0.01153  -0.0102   1.0000   1.0000
  -0.750  -0.0901   0.02088   0.01139  -0.0060   1.0000   1.0000
  -0.500  -0.0918   0.02098   0.01138  -0.0028   1.0000   1.0000
  -0.250  -0.0875   0.02122   0.01151  -0.0005   1.0000   1.0000
   0.000  -0.0791   0.02158   0.01176   0.0010   1.0000   1.0000
   0.250  -0.0682   0.02203   0.01212   0.0021   1.0000   1.0000
   0.500  -0.0558   0.02257   0.01258   0.0029   1.0000   1.0000
   0.750  -0.0425   0.02320   0.01314   0.0034   1.0000   1.0000
   1.000   0.0185   0.02438   0.01427  -0.0047   0.9836   1.0000
   1.250   0.0758   0.02535   0.01522  -0.0119   0.9631   1.0000
   1.500   0.1372   0.02626   0.01614  -0.0193   0.9438   1.0000
   1.750   0.1837   0.02691   0.01683  -0.0238   0.9216   1.0000
   2.000   0.2367   0.02747   0.01745  -0.0291   0.9003   1.0000
   2.250   0.2965   0.02782   0.01790  -0.0350   0.8803   1.0000
   2.500   0.3372   0.02818   0.01835  -0.0375   0.8573   1.0000
   2.750   0.3910   0.02822   0.01852  -0.0415   0.8360   1.0000
   3.000   0.4472   0.02791   0.01837  -0.0452   0.8159   1.0000
   3.250   0.4775   0.02806   0.01861  -0.0448   0.7916   1.0000
   3.500   0.5214   0.02763   0.01831  -0.0457   0.7694   1.0000
   3.750   0.5547   0.02742   0.01819  -0.0449   0.7454   1.0000
   4.000   0.5881   0.02707   0.01794  -0.0438   0.7208   1.0000
   4.250   0.6162   0.02691   0.01784  -0.0419   0.6949   1.0000
   4.500   0.6484   0.02644   0.01738  -0.0401   0.6691   1.0000
   4.750   0.6714   0.02646   0.01745  -0.0376   0.6395   1.0000
   5.000   0.6955   0.02641   0.01739  -0.0351   0.6088   1.0000
   5.250   0.7194   0.02636   0.01730  -0.0326   0.5762   1.0000
   5.500   0.7426   0.02638   0.01724  -0.0300   0.5417   1.0000
   5.750   0.7660   0.02644   0.01713  -0.0274   0.5055   1.0000
   6.000   0.7841   0.02688   0.01751  -0.0247   0.4655   1.0000
   6.250   0.8050   0.02718   0.01753  -0.0221   0.4246   1.0000
   6.500   0.8212   0.02783   0.01806  -0.0193   0.3812   1.0000
   6.750   0.8381   0.02860   0.01856  -0.0167   0.3392   1.0000
   7.000   0.8547   0.02959   0.01930  -0.0143   0.3001   1.0000
   7.250   0.8727   0.03088   0.02031  -0.0124   0.2665   1.0000
   7.500   0.8903   0.03247   0.02187  -0.0106   0.2386   1.0000
   7.750   0.9114   0.03420   0.02338  -0.0093   0.2171   1.0000
   8.000   0.9315   0.03624   0.02548  -0.0081   0.2012   1.0000
   8.250   0.9527   0.03827   0.02751  -0.0070   0.1882   1.0000
   8.500   0.9668   0.04062   0.03028  -0.0052   0.1783   1.0000
   8.750   0.9870   0.04319   0.03289  -0.0043   0.1712   1.0000
   9.000   0.9950   0.04637   0.03663  -0.0022   0.1667   1.0000
   9.250   1.0073   0.04921   0.03971  -0.0007   0.1617   1.0000
   9.500   1.0233   0.05216   0.04268   0.0002   0.1568   1.0000
   9.750   1.0172   0.05608   0.04717   0.0029   0.1549   1.0000
  10.000   1.0079   0.06045   0.05196   0.0051   0.1540   1.0000
  10.250   0.9926   0.06524   0.05710   0.0071   0.1542   1.0000
  10.500   0.9703   0.07043   0.06255   0.0087   0.1550   1.0000
  10.750   0.9445   0.07571   0.06799   0.0100   0.1561   1.0000
  11.000   0.9229   0.08150   0.07387   0.0099   0.1572   1.0000
  11.250   0.7325   0.11804   0.11023  -0.0187   0.1995   1.0000
  11.500   0.7469   0.12275   0.11499  -0.0186   0.2026   1.0000
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