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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 50,000
Max Cl/Cd: 28.73 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65410-il-50000.txt
Download as CSV file: xf-naca65410-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4158   0.10466   0.09768  -0.0249   1.0000   0.2809
  -8.750  -0.4165   0.10215   0.09524  -0.0242   1.0000   0.2968
  -8.500  -0.4229   0.10015   0.09335  -0.0234   1.0000   0.3128
  -8.250  -0.4027   0.09605   0.08924  -0.0212   1.0000   0.3381
  -8.000  -0.3948   0.09314   0.08638  -0.0191   1.0000   0.3636
  -7.750  -0.4118   0.09248   0.08588  -0.0169   1.0000   0.3855
  -7.500  -0.3796   0.08781   0.08113  -0.0145   1.0000   0.4207
  -7.250  -0.3711   0.08512   0.07849  -0.0122   1.0000   0.4495
  -7.000  -0.3615   0.08247   0.07589  -0.0098   1.0000   0.4791
  -6.750  -0.3521   0.07985   0.07332  -0.0075   1.0000   0.5089
  -6.500  -0.3428   0.07720   0.07072  -0.0053   1.0000   0.5359
  -5.000  -0.4950   0.04958   0.04266  -0.0361   1.0000   0.2149
  -4.750  -0.4581   0.04370   0.03541  -0.0407   1.0000   0.1559
  -4.500  -0.4320   0.04027   0.03133  -0.0409   1.0000   0.1395
  -4.250  -0.4081   0.03709   0.02780  -0.0408   1.0000   0.1322
  -4.000  -0.3801   0.03515   0.02492  -0.0406   1.0000   0.1264
  -3.750  -0.3567   0.03265   0.02231  -0.0403   1.0000   0.1295
  -3.500  -0.3314   0.03087   0.02018  -0.0398   1.0000   0.1302
  -3.250  -0.3066   0.02931   0.01834  -0.0389   1.0000   0.1310
  -3.000  -0.2834   0.02805   0.01691  -0.0377   1.0000   0.1343
  -2.750  -0.2615   0.02699   0.01574  -0.0363   1.0000   0.1436
  -2.500  -0.2409   0.02612   0.01478  -0.0346   1.0000   0.1531
  -2.250  -0.2194   0.02519   0.01386  -0.0333   1.0000   0.1653
  -2.000  -0.1958   0.02418   0.01298  -0.0330   1.0000   0.1949
  -1.750  -0.1813   0.02120   0.01291  -0.0299   1.0000   0.6889
  -1.500  -0.1743   0.02124   0.01322  -0.0178   1.0000   1.0000
  -1.250  -0.1634   0.02113   0.01271  -0.0164   1.0000   1.0000
  -1.000  -0.1465   0.02117   0.01235  -0.0162   1.0000   1.0000
  -0.750  -0.1262   0.02132   0.01217  -0.0165   1.0000   1.0000
  -0.500  -0.1044   0.02156   0.01211  -0.0170   1.0000   1.0000
  -0.250  -0.0817   0.02187   0.01215  -0.0177   1.0000   1.0000
   0.000  -0.0589   0.02224   0.01226  -0.0183   1.0000   1.0000
   0.250  -0.0361   0.02265   0.01246  -0.0189   1.0000   1.0000
   0.500  -0.0134   0.02310   0.01273  -0.0194   1.0000   1.0000
   0.750   0.0091   0.02359   0.01306  -0.0199   1.0000   1.0000
   1.000   0.0313   0.02412   0.01345  -0.0204   1.0000   1.0000
   1.250   0.0532   0.02469   0.01389  -0.0209   1.0000   1.0000
   1.500   0.0748   0.02529   0.01440  -0.0212   1.0000   1.0000
   1.750   0.0962   0.02593   0.01496  -0.0216   1.0000   1.0000
   2.000   0.1173   0.02661   0.01558  -0.0220   1.0000   1.0000
   2.250   0.1380   0.02733   0.01625  -0.0223   1.0000   1.0000
   2.500   0.1585   0.02808   0.01698  -0.0227   1.0000   1.0000
   2.750   0.1787   0.02888   0.01776  -0.0230   1.0000   1.0000
   3.000   0.1985   0.02972   0.01861  -0.0233   1.0000   1.0000
   3.250   0.2180   0.03061   0.01953  -0.0237   1.0000   1.0000
   3.500   0.2541   0.03208   0.02108  -0.0273   0.9908   1.0000
   3.750   0.2946   0.03371   0.02280  -0.0316   0.9776   1.0000
   4.000   0.3330   0.03525   0.02450  -0.0355   0.9639   1.0000
   4.250   0.3705   0.03674   0.02615  -0.0390   0.9489   1.0000
   4.500   0.4077   0.03821   0.02779  -0.0424   0.9329   1.0000
   4.750   0.4471   0.03969   0.02949  -0.0459   0.9156   1.0000
   5.000   0.4858   0.04109   0.03118  -0.0491   0.8965   1.0000
   5.250   0.5205   0.04228   0.03264  -0.0514   0.8751   1.0000
   5.500   0.5620   0.04340   0.03410  -0.0542   0.8507   1.0000
   5.750   0.6082   0.04411   0.03529  -0.0568   0.8216   1.0000
   6.000   0.7806   0.02717   0.01621  -0.0394   0.1870   1.0000
   6.250   0.7964   0.02936   0.01810  -0.0373   0.1575   1.0000
   6.500   0.8340   0.03158   0.02005  -0.0379   0.1330   1.0000
   6.750   0.8960   0.03462   0.02298  -0.0413   0.1199   1.0000
   7.000   0.9312   0.03699   0.02580  -0.0415   0.1124   1.0000
   7.250   0.9667   0.04043   0.02927  -0.0424   0.1071   1.0000
   7.500   0.9967   0.04423   0.03338  -0.0423   0.1065   1.0000
   7.750   1.0184   0.04716   0.03698  -0.0407   0.1078   1.0000
   8.000   1.0326   0.05054   0.04112  -0.0384   0.1100   1.0000
   8.250   1.0441   0.05437   0.04551  -0.0364   0.1112   1.0000
   8.500   1.0503   0.05845   0.05019  -0.0342   0.1132   1.0000
   8.750   1.0550   0.06297   0.05514  -0.0323   0.1163   1.0000
   9.000   1.0580   0.06762   0.06024  -0.0305   0.1228   1.0000
   9.250   1.0464   0.07298   0.06606  -0.0285   0.1307   1.0000
   9.500   1.0568   0.08075   0.07406  -0.0287   0.1474   1.0000
   9.750   1.0290   0.08648   0.08019  -0.0277   0.1611   1.0000
  10.000   0.9838   0.08983   0.08365  -0.0260   0.1601   1.0000
  10.250   0.9329   0.09583   0.08973  -0.0288   0.1642   1.0000
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