Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-112 (naca641112-il)
Reynolds number: 100,000
Max Cl/Cd: 39.95 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca641112-il-100000-n5.txt
Download as CSV file: xf-naca641112-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-112                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6717   0.08614   0.08095  -0.0256   1.0000   0.0319
 -11.250  -0.6957   0.07784   0.07260  -0.0314   1.0000   0.0314
 -11.000  -0.7207   0.07104   0.06568  -0.0358   1.0000   0.0311
 -10.750  -0.7428   0.06567   0.06015  -0.0383   1.0000   0.0308
 -10.500  -0.7628   0.06134   0.05564  -0.0392   1.0000   0.0309
 -10.250  -0.7807   0.05768   0.05180  -0.0385   1.0000   0.0309
 -10.000  -0.7943   0.05432   0.04820  -0.0369   1.0000   0.0310
  -9.750  -0.8010   0.05083   0.04441  -0.0355   1.0000   0.0311
  -9.500  -0.8028   0.04741   0.04065  -0.0341   1.0000   0.0312
  -9.250  -0.7999   0.04418   0.03703  -0.0326   1.0000   0.0315
  -9.000  -0.7924   0.04119   0.03365  -0.0312   1.0000   0.0319
  -8.750  -0.7813   0.03843   0.03047  -0.0299   1.0000   0.0324
  -8.500  -0.7672   0.03606   0.02769  -0.0287   1.0000   0.0332
  -8.250  -0.7511   0.03400   0.02528  -0.0275   1.0000   0.0343
  -8.000  -0.7328   0.03204   0.02327  -0.0269   1.0000   0.0357
  -7.750  -0.7135   0.03046   0.02156  -0.0261   1.0000   0.0369
  -7.500  -0.6933   0.02888   0.01982  -0.0251   1.0000   0.0380
  -7.250  -0.6732   0.02745   0.01826  -0.0241   1.0000   0.0392
  -7.000  -0.6540   0.02616   0.01686  -0.0228   1.0000   0.0406
  -6.750  -0.6364   0.02513   0.01571  -0.0213   1.0000   0.0426
  -6.500  -0.6217   0.02409   0.01464  -0.0194   1.0000   0.0447
  -6.000  -0.5831   0.02221   0.01278  -0.0177   0.9926   0.0500
  -5.750  -0.5490   0.02126   0.01169  -0.0196   0.9836   0.0545
  -5.500  -0.5159   0.02021   0.01069  -0.0216   0.9746   0.0613
  -5.250  -0.4838   0.01932   0.00972  -0.0231   0.9649   0.0693
  -5.000  -0.4526   0.01845   0.00889  -0.0245   0.9550   0.0847
  -4.750  -0.4225   0.01743   0.00805  -0.0258   0.9456   0.1213
  -4.500  -0.3997   0.01567   0.00716  -0.0265   0.9348   0.2753
  -4.250  -0.3799   0.01462   0.00706  -0.0256   0.9231   0.4755
  -4.000  -0.3527   0.01452   0.00708  -0.0252   0.9132   0.5460
  -3.750  -0.3252   0.01459   0.00719  -0.0246   0.9042   0.5971
  -3.500  -0.3013   0.01485   0.00749  -0.0230   0.8934   0.6405
  -3.250  -0.2762   0.01514   0.00779  -0.0215   0.8843   0.6719
  -3.000  -0.2499   0.01524   0.00780  -0.0207   0.8752   0.6893
  -2.750  -0.2233   0.01521   0.00766  -0.0202   0.8655   0.6977
  -2.500  -0.1955   0.01513   0.00743  -0.0201   0.8577   0.7074
  -2.250  -0.1692   0.01511   0.00736  -0.0196   0.8480   0.7143
  -2.000  -0.1420   0.01503   0.00716  -0.0195   0.8398   0.7231
  -1.750  -0.1152   0.01499   0.00706  -0.0191   0.8312   0.7289
  -1.500  -0.0883   0.01492   0.00690  -0.0190   0.8230   0.7370
  -1.250  -0.0615   0.01488   0.00682  -0.0186   0.8150   0.7430
  -1.000  -0.0348   0.01484   0.00672  -0.0184   0.8068   0.7504
  -0.750  -0.0080   0.01481   0.00665  -0.0181   0.7994   0.7572
  -0.500   0.0185   0.01480   0.00662  -0.0178   0.7916   0.7648
  -0.250   0.0452   0.01478   0.00657  -0.0175   0.7843   0.7721
   0.000   0.0717   0.01479   0.00657  -0.0172   0.7767   0.7795
   0.250   0.0983   0.01479   0.00657  -0.0169   0.7695   0.7873
   0.500   0.1248   0.01481   0.00660  -0.0165   0.7628   0.7954
   0.750   0.1511   0.01484   0.00666  -0.0162   0.7555   0.8034
   1.000   0.1778   0.01486   0.00668  -0.0159   0.7493   0.8120
   1.250   0.2040   0.01492   0.00681  -0.0156   0.7416   0.8200
   1.500   0.2308   0.01495   0.00685  -0.0153   0.7363   0.8299
   1.750   0.2564   0.01504   0.00703  -0.0148   0.7286   0.8380
   2.000   0.2828   0.01508   0.00713  -0.0144   0.7225   0.8476
   2.250   0.3087   0.01517   0.00731  -0.0140   0.7157   0.8573
   2.500   0.3349   0.01523   0.00744  -0.0135   0.7085   0.8668
   2.750   0.3608   0.01529   0.00760  -0.0131   0.7008   0.8775
   3.000   0.3871   0.01533   0.00774  -0.0126   0.6929   0.8883
   3.250   0.4141   0.01540   0.00794  -0.0123   0.6849   0.8989
   3.500   0.4419   0.01540   0.00805  -0.0120   0.6762   0.9101
   3.750   0.4694   0.01526   0.00797  -0.0114   0.6600   0.9221
   4.000   0.4966   0.01499   0.00775  -0.0107   0.6320   0.9345
   4.250   0.5258   0.01471   0.00745  -0.0103   0.5904   0.9463
   4.500   0.5568   0.01462   0.00730  -0.0106   0.5399   0.9584
   4.750   0.5893   0.01475   0.00734  -0.0115   0.4732   0.9710
   5.000   0.6131   0.01599   0.00754  -0.0118   0.2752   0.9880
   5.250   0.6256   0.01765   0.00844  -0.0108   0.1459   1.0000
   5.500   0.6372   0.01873   0.00919  -0.0088   0.0996   1.0000
   5.750   0.6530   0.01967   0.00998  -0.0074   0.0790   1.0000
   6.000   0.6701   0.02060   0.01083  -0.0062   0.0686   1.0000
   6.250   0.6893   0.02139   0.01168  -0.0051   0.0608   1.0000
   6.500   0.7068   0.02238   0.01266  -0.0040   0.0555   1.0000
   6.750   0.7259   0.02330   0.01366  -0.0030   0.0515   1.0000
   7.000   0.7446   0.02428   0.01463  -0.0020   0.0476   1.0000
   7.250   0.7633   0.02547   0.01582  -0.0011   0.0446   1.0000
   7.500   0.7846   0.02664   0.01709  -0.0003   0.0423   1.0000
   7.750   0.8068   0.02795   0.01849   0.0003   0.0404   1.0000
   8.000   0.8291   0.02928   0.01988   0.0008   0.0386   1.0000
   8.250   0.8508   0.03077   0.02135   0.0011   0.0367   1.0000
   8.500   0.8732   0.03255   0.02328   0.0015   0.0349   1.0000
   8.750   0.8953   0.03437   0.02539   0.0021   0.0338   1.0000
   9.000   0.9157   0.03649   0.02779   0.0028   0.0329   1.0000
   9.250   0.9334   0.03880   0.03041   0.0037   0.0321   1.0000
   9.500   0.9480   0.04128   0.03322   0.0047   0.0315   1.0000
   9.750   0.9590   0.04397   0.03625   0.0060   0.0310   1.0000
  10.000   0.9666   0.04663   0.03923   0.0074   0.0305   1.0000
  10.250   0.9724   0.04907   0.04191   0.0088   0.0298   1.0000
  10.500   0.9766   0.05137   0.04441   0.0101   0.0291   1.0000
  10.750   0.9774   0.05362   0.04680   0.0117   0.0284   1.0000
  11.000   0.9729   0.05635   0.04969   0.0133   0.0280   1.0000
  11.250   0.9643   0.05956   0.05307   0.0147   0.0277   1.0000
  11.750   0.9343   0.06719   0.06112   0.0156   0.0275   1.0000
  12.000   0.9166   0.07166   0.06580   0.0148   0.0276   1.0000
<< Back to NACA 64(1)-112 (naca641112-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(1)-112 (naca641112-il)