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

NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 200,000
Max Cl/Cd: 67.93 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651412-il-200000-n5.txt
Download as CSV file: xf-naca651412-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4585   0.08571   0.08206  -0.0540   1.0000   0.0188
 -10.250  -0.4696   0.07899   0.07539  -0.0577   1.0000   0.0187
 -10.000  -0.4825   0.07211   0.06855  -0.0623   1.0000   0.0185
  -9.750  -0.5025   0.06639   0.06282  -0.0654   1.0000   0.0183
  -9.500  -0.5274   0.06272   0.05916  -0.0652   1.0000   0.0181
  -9.250  -0.5447   0.05815   0.05448  -0.0676   0.9908   0.0180
  -9.000  -0.5469   0.05107   0.04705  -0.0731   0.9779   0.0180
  -8.750  -0.5434   0.04465   0.04018  -0.0763   0.9677   0.0182
  -8.500  -0.5353   0.03884   0.03379  -0.0780   0.9585   0.0185
  -8.250  -0.5201   0.03400   0.02829  -0.0792   0.9509   0.0190
  -8.000  -0.5011   0.03158   0.02559  -0.0797   0.9428   0.0200
  -7.750  -0.4752   0.03014   0.02400  -0.0809   0.9371   0.0208
  -7.500  -0.4517   0.02836   0.02196  -0.0813   0.9301   0.0217
  -7.250  -0.4278   0.02618   0.01941  -0.0814   0.9233   0.0224
  -7.000  -0.4024   0.02431   0.01718  -0.0816   0.9171   0.0232
  -6.750  -0.3776   0.02286   0.01543  -0.0813   0.9098   0.0241
  -6.500  -0.3496   0.02180   0.01406  -0.0816   0.9047   0.0255
  -6.250  -0.3265   0.02031   0.01249  -0.0812   0.8968   0.0264
  -6.000  -0.2999   0.01928   0.01135  -0.0812   0.8911   0.0273
  -5.750  -0.2753   0.01844   0.01043  -0.0809   0.8841   0.0282
  -5.500  -0.2497   0.01767   0.00958  -0.0806   0.8778   0.0294
  -5.250  -0.2243   0.01705   0.00888  -0.0803   0.8715   0.0313
  -5.000  -0.1994   0.01647   0.00820  -0.0799   0.8646   0.0327
  -4.750  -0.1742   0.01578   0.00743  -0.0796   0.8591   0.0337
  -4.500  -0.1514   0.01501   0.00665  -0.0791   0.8519   0.0355
  -4.250  -0.1259   0.01449   0.00607  -0.0789   0.8464   0.0377
  -4.000  -0.1004   0.01412   0.00564  -0.0787   0.8400   0.0410
  -3.750  -0.0744   0.01376   0.00519  -0.0786   0.8338   0.0444
  -3.500  -0.0480   0.01333   0.00471  -0.0785   0.8287   0.0499
  -3.250  -0.0221   0.01299   0.00436  -0.0784   0.8223   0.0599
  -3.000   0.0034   0.01236   0.00399  -0.0785   0.8171   0.1225
  -2.750   0.0248   0.01080   0.00356  -0.0788   0.8114   0.4087
  -2.500   0.0479   0.01031   0.00372  -0.0780   0.8054   0.5941
  -2.250   0.0734   0.01033   0.00388  -0.0771   0.8007   0.6628
  -2.000   0.0984   0.01046   0.00408  -0.0761   0.7952   0.7023
  -1.750   0.1243   0.01056   0.00417  -0.0755   0.7899   0.7220
  -1.500   0.1523   0.01058   0.00410  -0.0754   0.7855   0.7322
  -1.250   0.1796   0.01058   0.00406  -0.0754   0.7800   0.7372
  -1.000   0.2077   0.01058   0.00399  -0.0755   0.7748   0.7431
  -0.750   0.2360   0.01058   0.00393  -0.0756   0.7707   0.7480
  -0.500   0.2634   0.01060   0.00393  -0.0756   0.7655   0.7531
  -0.250   0.2914   0.01062   0.00391  -0.0758   0.7603   0.7591
   0.000   0.3193   0.01063   0.00390  -0.0758   0.7561   0.7639
   0.250   0.3468   0.01067   0.00394  -0.0758   0.7513   0.7692
   0.500   0.3747   0.01071   0.00396  -0.0759   0.7462   0.7754
   0.750   0.4022   0.01073   0.00400  -0.0759   0.7419   0.7802
   1.000   0.4298   0.01078   0.00406  -0.0759   0.7375   0.7860
   1.250   0.4573   0.01084   0.00415  -0.0760   0.7323   0.7921
   1.500   0.4844   0.01088   0.00423  -0.0758   0.7279   0.7972
   1.750   0.5124   0.01094   0.00431  -0.0759   0.7239   0.8036
   2.000   0.5388   0.01102   0.00446  -0.0757   0.7185   0.8095
   2.250   0.5658   0.01108   0.00458  -0.0756   0.7139   0.8155
   2.500   0.5942   0.01115   0.00468  -0.0757   0.7100   0.8223
   2.750   0.6194   0.01123   0.00488  -0.0753   0.7041   0.8283
   3.000   0.6465   0.01129   0.00500  -0.0752   0.6980   0.8358
   3.250   0.6717   0.01133   0.00513  -0.0746   0.6895   0.8420
   3.500   0.6972   0.01132   0.00515  -0.0739   0.6766   0.8494
   3.750   0.7202   0.01127   0.00514  -0.0727   0.6568   0.8566
   4.000   0.7422   0.01123   0.00506  -0.0712   0.6247   0.8653
   4.250   0.7614   0.01129   0.00501  -0.0691   0.5798   0.8734
   4.500   0.7812   0.01150   0.00508  -0.0674   0.5284   0.8828
   4.750   0.7918   0.01213   0.00526  -0.0641   0.4269   0.8936
   5.000   0.7928   0.01347   0.00589  -0.0596   0.2915   0.9078
   5.250   0.7968   0.01474   0.00663  -0.0560   0.1814   0.9243
   5.500   0.8033   0.01594   0.00735  -0.0528   0.0909   0.9447
   5.750   0.8221   0.01682   0.00803  -0.0519   0.0538   0.9737
   6.000   0.8432   0.01751   0.00868  -0.0514   0.0432   1.0000
   6.250   0.8634   0.01818   0.00936  -0.0506   0.0375   1.0000
   6.500   0.8813   0.01896   0.01018  -0.0494   0.0337   1.0000
   6.750   0.8988   0.01964   0.01095  -0.0481   0.0315   1.0000
   7.000   0.9152   0.02041   0.01177  -0.0467   0.0295   1.0000
   7.250   0.9303   0.02127   0.01265  -0.0452   0.0276   1.0000
   7.500   0.9415   0.02246   0.01385  -0.0432   0.0259   1.0000
   7.750   0.9582   0.02328   0.01477  -0.0419   0.0248   1.0000
   8.000   0.9736   0.02428   0.01585  -0.0406   0.0239   1.0000
   8.250   0.9896   0.02533   0.01697  -0.0393   0.0230   1.0000
   8.500   1.0062   0.02643   0.01813  -0.0382   0.0222   1.0000
   8.750   1.0237   0.02757   0.01934  -0.0371   0.0215   1.0000
   9.000   1.0420   0.02877   0.02059  -0.0363   0.0210   1.0000
   9.250   1.0613   0.03007   0.02194  -0.0356   0.0204   1.0000
   9.500   1.0831   0.03164   0.02355  -0.0352   0.0199   1.0000
   9.750   1.1076   0.03352   0.02556  -0.0352   0.0193   1.0000
  10.000   1.1254   0.03486   0.02713  -0.0343   0.0188   1.0000
  10.250   1.1427   0.03644   0.02893  -0.0334   0.0181   1.0000
  10.500   1.1593   0.03835   0.03109  -0.0325   0.0177   1.0000
  10.750   1.1729   0.04046   0.03345  -0.0313   0.0173   1.0000
  11.000   1.1830   0.04274   0.03600  -0.0299   0.0171   1.0000
  11.250   1.1891   0.04515   0.03867  -0.0282   0.0168   1.0000
  11.500   1.1915   0.04773   0.04152  -0.0263   0.0165   1.0000
  11.750   1.1907   0.05050   0.04455  -0.0245   0.0164   1.0000
  12.000   1.1871   0.05340   0.04771  -0.0228   0.0162   1.0000
  12.250   1.1818   0.05639   0.05094  -0.0213   0.0160   1.0000
  12.500   1.1767   0.05931   0.05404  -0.0202   0.0158   1.0000
  12.750   1.1694   0.06250   0.05742  -0.0194   0.0155   1.0000
  13.000   1.1608   0.06593   0.06102  -0.0191   0.0154   1.0000
  13.250   1.1487   0.07004   0.06534  -0.0191   0.0152   1.0000
  13.500   1.1370   0.07424   0.06971  -0.0196   0.0151   1.0000
  13.750   1.1207   0.07940   0.07506  -0.0208   0.0150   1.0000
  14.000   1.1018   0.08529   0.08116  -0.0228   0.0150   1.0000
  14.250   1.0800   0.09217   0.08826  -0.0258   0.0150   1.0000
  14.500   1.0433   0.10297   0.09937  -0.0317   0.0152   1.0000
<< Back to NACA 65(1)-412 (naca651412-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(1)-412 (naca651412-il)