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NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-210 (naca66210-il)
Reynolds number: 50,000
Max Cl/Cd: 27.57 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66210-il-50000-n5.txt
Download as CSV file: xf-naca66210-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-210                                     
  
 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  -0.4204   0.09617   0.08943  -0.0418   1.0000   0.0656
 -10.000  -0.5271   0.09890   0.09182  -0.0446   1.0000   0.0667
  -9.750  -0.5147   0.09542   0.08834  -0.0422   1.0000   0.0643
  -9.500  -0.5167   0.09074   0.08372  -0.0440   1.0000   0.0616
  -9.250  -0.5266   0.08560   0.07865  -0.0471   1.0000   0.0593
  -8.750  -0.5818   0.07777   0.07073  -0.0484   1.0000   0.0536
  -8.500  -0.5862   0.07436   0.06734  -0.0468   1.0000   0.0530
  -8.250  -0.5934   0.07125   0.06422  -0.0447   1.0000   0.0523
  -8.000  -0.6019   0.06834   0.06126  -0.0423   1.0000   0.0517
  -7.750  -0.6107   0.06544   0.05827  -0.0394   1.0000   0.0510
  -7.500  -0.6181   0.06262   0.05532  -0.0365   1.0000   0.0505
  -7.250  -0.6236   0.05973   0.05224  -0.0336   1.0000   0.0498
  -7.000  -0.6267   0.05678   0.04907  -0.0307   1.0000   0.0493
  -6.750  -0.6271   0.05379   0.04580  -0.0279   1.0000   0.0488
  -6.500  -0.6244   0.05083   0.04250  -0.0253   1.0000   0.0485
  -6.250  -0.6188   0.04795   0.03926  -0.0229   1.0000   0.0486
  -6.000  -0.6105   0.04532   0.03618  -0.0206   1.0000   0.0502
  -5.750  -0.5992   0.04285   0.03321  -0.0185   1.0000   0.0519
  -5.500  -0.5851   0.04042   0.03027  -0.0165   1.0000   0.0528
  -5.250  -0.5683   0.03808   0.02745  -0.0149   1.0000   0.0530
  -5.000  -0.5496   0.03594   0.02487  -0.0133   1.0000   0.0535
  -4.750  -0.5292   0.03399   0.02254  -0.0119   1.0000   0.0543
  -4.500  -0.5088   0.03200   0.02043  -0.0109   1.0000   0.0566
  -4.250  -0.4881   0.03071   0.01901  -0.0098   1.0000   0.0610
  -4.000  -0.4653   0.02948   0.01752  -0.0086   1.0000   0.0643
  -3.750  -0.4420   0.02841   0.01618  -0.0072   1.0000   0.0664
  -3.500  -0.4204   0.02734   0.01504  -0.0058   1.0000   0.0692
  -3.250  -0.4008   0.02653   0.01414  -0.0045   1.0000   0.0756
  -3.000  -0.3817   0.02576   0.01325  -0.0031   1.0000   0.0836
  -2.750  -0.3547   0.02497   0.01232  -0.0034   0.9970   0.0927
  -2.500  -0.3284   0.02417   0.01142  -0.0037   0.9938   0.1089
  -2.250  -0.3111   0.02165   0.01053  -0.0036   0.9911   0.3375
  -2.000  -0.1404   0.02361   0.01363  -0.0178   1.0000   0.9939
  -1.750  -0.1143   0.02349   0.01327  -0.0189   1.0000   1.0000
  -1.500  -0.1092   0.02338   0.01302  -0.0160   1.0000   1.0000
  -1.250  -0.0909   0.02332   0.01280  -0.0156   0.9968   1.0000
  -1.000  -0.0664   0.02333   0.01265  -0.0163   0.9918   1.0000
  -0.750  -0.0420   0.02339   0.01255  -0.0170   0.9870   1.0000
  -0.500  -0.0197   0.02344   0.01248  -0.0172   0.9819   1.0000
  -0.250   0.0044   0.02355   0.01250  -0.0178   0.9770   1.0000
   0.000   0.0258   0.02364   0.01250  -0.0177   0.9716   1.0000
   0.250   0.0494   0.02379   0.01259  -0.0181   0.9663   1.0000
   0.500   0.0708   0.02394   0.01269  -0.0180   0.9606   1.0000
   0.750   0.0933   0.02411   0.01285  -0.0181   0.9546   1.0000
   1.000   0.1164   0.02433   0.01305  -0.0182   0.9489   1.0000
   1.250   0.1360   0.02451   0.01324  -0.0177   0.9421   1.0000
   1.500   0.1643   0.02483   0.01358  -0.0187   0.9369   1.0000
   1.750   0.1795   0.02499   0.01378  -0.0173   0.9290   1.0000
   2.000   0.2090   0.02535   0.01421  -0.0185   0.9234   1.0000
   2.250   0.2249   0.02556   0.01448  -0.0171   0.9149   1.0000
   2.500   0.2571   0.02596   0.01498  -0.0187   0.9091   1.0000
   2.750   0.2744   0.02622   0.01533  -0.0175   0.8997   1.0000
   3.000   0.3029   0.02658   0.01586  -0.0182   0.8920   1.0000
   3.250   0.3302   0.02692   0.01636  -0.0187   0.8831   1.0000
   3.500   0.3548   0.02725   0.01686  -0.0187   0.8728   1.0000
   3.750   0.3859   0.02757   0.01742  -0.0197   0.8627   1.0000
   4.000   0.4240   0.02781   0.01802  -0.0216   0.8524   1.0000
   4.250   0.4552   0.02782   0.01836  -0.0219   0.8359   1.0000
   4.500   0.5683   0.02061   0.01045  -0.0200   0.4068   1.0000
   4.750   0.5535   0.02292   0.01120  -0.0135   0.1815   1.0000
   5.000   0.5566   0.02470   0.01227  -0.0100   0.1145   1.0000
   5.250   0.5689   0.02591   0.01335  -0.0078   0.0925   1.0000
   5.500   0.5842   0.02707   0.01454  -0.0059   0.0835   1.0000
   5.750   0.6028   0.02826   0.01581  -0.0045   0.0767   1.0000
   6.000   0.6272   0.02952   0.01724  -0.0039   0.0693   1.0000
   6.250   0.6593   0.03096   0.01875  -0.0044   0.0623   1.0000
   6.500   0.7025   0.03300   0.02096  -0.0061   0.0591   1.0000
   6.750   0.7382   0.03510   0.02339  -0.0069   0.0562   1.0000
   7.000   0.7650   0.03709   0.02561  -0.0067   0.0521   1.0000
   7.250   0.7897   0.03953   0.02825  -0.0066   0.0493   1.0000
   7.500   0.8131   0.04271   0.03169  -0.0062   0.0484   1.0000
   7.750   0.8313   0.04554   0.03501  -0.0048   0.0480   1.0000
   8.000   0.8457   0.04862   0.03857  -0.0031   0.0477   1.0000
   8.250   0.8568   0.05185   0.04224  -0.0013   0.0476   1.0000
   8.500   0.8638   0.05513   0.04598   0.0009   0.0473   1.0000
   8.750   0.8657   0.05840   0.04972   0.0034   0.0465   1.0000
   9.000   0.8638   0.06176   0.05350   0.0058   0.0457   1.0000
   9.250   0.8583   0.06521   0.05730   0.0081   0.0451   1.0000
   9.500   0.8498   0.06877   0.06114   0.0103   0.0449   1.0000
   9.750   0.8369   0.07223   0.06482   0.0125   0.0449   1.0000
  10.000   0.8216   0.07584   0.06859   0.0142   0.0450   1.0000
  10.250   0.8047   0.07983   0.07272   0.0148   0.0452   1.0000
  10.500   0.7877   0.08431   0.07731   0.0143   0.0456   1.0000
  10.750   0.7712   0.08936   0.08242   0.0126   0.0459   1.0000
  11.000   0.7569   0.09492   0.08803   0.0100   0.0464   1.0000
  11.250   0.7454   0.10090   0.09404   0.0067   0.0469   1.0000
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