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

NACA 1410 (naca1410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 1410 (naca1410-il)
Reynolds number: 50,000
Max Cl/Cd: 31.56 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1410-il-50000-n5.txt
Download as CSV file: xf-naca1410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1410                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6451   0.09163   0.08427  -0.0199   1.0000   0.0655
 -10.000  -0.6606   0.08314   0.07580  -0.0264   1.0000   0.0652
  -9.750  -0.6812   0.07590   0.06859  -0.0317   1.0000   0.0647
  -9.500  -0.7025   0.07015   0.06275  -0.0339   1.0000   0.0645
  -9.250  -0.7196   0.06458   0.05697  -0.0353   1.0000   0.0646
  -9.000  -0.7316   0.05934   0.05140  -0.0357   1.0000   0.0651
  -8.750  -0.7376   0.05443   0.04604  -0.0353   1.0000   0.0658
  -8.500  -0.7383   0.04990   0.04093  -0.0344   1.0000   0.0667
  -8.250  -0.7258   0.04739   0.03834  -0.0336   1.0000   0.0693
  -8.000  -0.7121   0.04521   0.03600  -0.0327   1.0000   0.0725
  -7.750  -0.6999   0.04224   0.03261  -0.0315   1.0000   0.0753
  -7.500  -0.6857   0.03921   0.02906  -0.0303   1.0000   0.0775
  -7.250  -0.6690   0.03677   0.02620  -0.0292   1.0000   0.0811
  -7.000  -0.6498   0.03519   0.02457  -0.0283   1.0000   0.0853
  -6.750  -0.6297   0.03328   0.02235  -0.0272   1.0000   0.0892
  -6.500  -0.6080   0.03139   0.02003  -0.0261   1.0000   0.0928
  -6.250  -0.5868   0.02991   0.01856  -0.0251   1.0000   0.0974
  -6.000  -0.5654   0.02870   0.01719  -0.0241   1.0000   0.1048
  -5.750  -0.5436   0.02743   0.01586  -0.0230   1.0000   0.1116
  -5.500  -0.5214   0.02625   0.01455  -0.0219   1.0000   0.1197
  -5.250  -0.5001   0.02515   0.01347  -0.0207   1.0000   0.1299
  -5.000  -0.4788   0.02418   0.01251  -0.0197   1.0000   0.1466
  -4.750  -0.4575   0.02322   0.01161  -0.0187   1.0000   0.1684
  -4.500  -0.4362   0.02231   0.01082  -0.0178   1.0000   0.1991
  -4.250  -0.4149   0.02147   0.01016  -0.0169   1.0000   0.2419
  -4.000  -0.3946   0.02063   0.00955  -0.0159   1.0000   0.2941
  -3.750  -0.3754   0.01977   0.00906  -0.0146   1.0000   0.3540
  -3.500  -0.3568   0.01910   0.00880  -0.0129   1.0000   0.4298
  -3.250  -0.3376   0.01862   0.00855  -0.0111   1.0000   0.5113
  -3.000  -0.3189   0.01816   0.00839  -0.0089   1.0000   0.5839
  -2.750  -0.3003   0.01783   0.00833  -0.0063   1.0000   0.6568
  -2.500  -0.2808   0.01761   0.00830  -0.0037   1.0000   0.7274
  -2.250  -0.2576   0.01751   0.00832  -0.0017   1.0000   0.7961
  -2.000  -0.2245   0.01754   0.00834  -0.0017   1.0000   0.8637
  -1.750  -0.1767   0.01763   0.00829  -0.0050   1.0000   0.9258
  -1.500  -0.1181   0.01769   0.00814  -0.0112   1.0000   0.9763
  -1.250  -0.0780   0.01762   0.00789  -0.0147   1.0000   1.0000
  -1.000  -0.0726   0.01759   0.00775  -0.0118   1.0000   1.0000
  -0.750  -0.0637   0.01765   0.00769  -0.0094   1.0000   1.0000
  -0.500  -0.0521   0.01779   0.00771  -0.0075   1.0000   1.0000
  -0.250  -0.0148   0.01801   0.00782  -0.0103   0.9905   1.0000
   0.000   0.0309   0.01824   0.00796  -0.0146   0.9768   1.0000
   0.250   0.0762   0.01844   0.00809  -0.0187   0.9627   1.0000
   0.500   0.1209   0.01859   0.00822  -0.0225   0.9480   1.0000
   0.750   0.1653   0.01871   0.00833  -0.0261   0.9327   1.0000
   1.000   0.2088   0.01879   0.00843  -0.0293   0.9169   1.0000
   1.250   0.2477   0.01883   0.00851  -0.0314   0.8990   1.0000
   1.500   0.2836   0.01887   0.00859  -0.0329   0.8795   1.0000
   1.750   0.3196   0.01887   0.00865  -0.0341   0.8599   1.0000
   2.000   0.3543   0.01885   0.00868  -0.0349   0.8397   1.0000
   2.250   0.3841   0.01888   0.00875  -0.0348   0.8163   1.0000
   2.500   0.4150   0.01887   0.00880  -0.0346   0.7939   1.0000
   2.750   0.4422   0.01893   0.00890  -0.0338   0.7688   1.0000
   3.000   0.4690   0.01900   0.00902  -0.0329   0.7434   1.0000
   3.250   0.4956   0.01908   0.00910  -0.0318   0.7174   1.0000
   3.500   0.5203   0.01921   0.00925  -0.0304   0.6889   1.0000
   3.750   0.5443   0.01938   0.00943  -0.0289   0.6589   1.0000
   4.000   0.5678   0.01958   0.00962  -0.0274   0.6275   1.0000
   4.250   0.5909   0.01984   0.00985  -0.0258   0.5939   1.0000
   4.500   0.6131   0.02014   0.01012  -0.0241   0.5568   1.0000
   4.750   0.6346   0.02048   0.01040  -0.0224   0.5168   1.0000
   5.000   0.6552   0.02089   0.01072  -0.0206   0.4735   1.0000
   5.250   0.6750   0.02139   0.01111  -0.0188   0.4263   1.0000
   5.500   0.6935   0.02200   0.01159  -0.0170   0.3716   1.0000
   5.750   0.7106   0.02280   0.01211  -0.0152   0.3095   1.0000
   6.000   0.7271   0.02385   0.01282  -0.0136   0.2484   1.0000
   6.250   0.7442   0.02509   0.01377  -0.0123   0.1991   1.0000
   6.500   0.7620   0.02644   0.01493  -0.0111   0.1640   1.0000
   6.750   0.7797   0.02784   0.01620  -0.0099   0.1403   1.0000
   7.000   0.7985   0.02919   0.01753  -0.0087   0.1233   1.0000
   7.250   0.8177   0.03062   0.01891  -0.0075   0.1132   1.0000
   7.500   0.8393   0.03204   0.02049  -0.0064   0.1050   1.0000
   7.750   0.8603   0.03356   0.02206  -0.0055   0.0984   1.0000
   8.000   0.8815   0.03504   0.02373  -0.0046   0.0913   1.0000
   8.250   0.9028   0.03676   0.02537  -0.0039   0.0867   1.0000
   8.500   0.9253   0.03881   0.02782  -0.0030   0.0831   1.0000
   8.750   0.9449   0.04091   0.03021  -0.0020   0.0792   1.0000
   9.000   0.9629   0.04277   0.03214  -0.0012   0.0751   1.0000
   9.250   0.9781   0.04531   0.03502   0.0000   0.0720   1.0000
   9.500   0.9895   0.04835   0.03856   0.0014   0.0698   1.0000
   9.750   0.9975   0.05133   0.04195   0.0029   0.0673   1.0000
  10.000   1.0050   0.05392   0.04478   0.0043   0.0645   1.0000
  10.250   1.0146   0.05634   0.04726   0.0053   0.0621   1.0000
  10.500   1.0136   0.05996   0.05116   0.0068   0.0609   1.0000
  10.750   1.0017   0.06402   0.05565   0.0086   0.0604   1.0000
  11.000   0.9833   0.06805   0.05999   0.0104   0.0601   1.0000
  11.250   0.9614   0.07258   0.06477   0.0109   0.0600   1.0000
  11.500   0.9374   0.07798   0.07037   0.0096   0.0601   1.0000
  11.750   0.9122   0.08451   0.07705   0.0063   0.0603   1.0000
  12.000   0.8867   0.09228   0.08493   0.0014   0.0607   1.0000
  12.250   0.8625   0.10114   0.09384  -0.0044   0.0611   1.0000
<< Back to NACA 1410 (naca1410-il)

Polar data table (+)

Polar graphs


<< Back to NACA 1410 (naca1410-il)