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

NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(3)-218 (naca663218-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.21 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca663218-il-1000000-n5.txt
Download as CSV file: xf-naca663218-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(3)-218                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -1.0250   0.07545   0.07189  -0.0805   0.9674   0.0119
 -19.250  -1.0175   0.07056   0.06686  -0.0860   0.9608   0.0120
 -19.000  -1.0098   0.06579   0.06193  -0.0913   0.9538   0.0121
 -18.750  -0.9992   0.06162   0.05761  -0.0962   0.9441   0.0122
 -18.500  -0.9929   0.05796   0.05377  -0.0995   0.9285   0.0122
 -18.250  -0.9904   0.05512   0.05076  -0.1007   0.9130   0.0123
 -18.000  -0.9909   0.05238   0.04787  -0.1011   0.8995   0.0123
 -17.750  -0.9891   0.05006   0.04540  -0.1012   0.8875   0.0124
 -17.500  -0.9859   0.04793   0.04316  -0.1012   0.8788   0.0125
 -17.250  -0.9847   0.04571   0.04080  -0.1009   0.8707   0.0125
 -17.000  -0.9805   0.04380   0.03879  -0.1006   0.8642   0.0125
 -16.750  -0.9748   0.04207   0.03695  -0.1003   0.8578   0.0126
 -16.500  -0.9694   0.04039   0.03515  -0.0998   0.8518   0.0127
 -16.250  -0.9626   0.03883   0.03351  -0.0993   0.8469   0.0127
 -16.000  -0.9574   0.03719   0.03177  -0.0986   0.8417   0.0128
 -15.750  -0.9534   0.03552   0.03001  -0.0977   0.8365   0.0129
 -15.500  -0.9464   0.03412   0.02852  -0.0968   0.8321   0.0130
 -15.250  -0.9379   0.03284   0.02716  -0.0961   0.8280   0.0130
 -15.000  -0.9298   0.03156   0.02583  -0.0951   0.8237   0.0132
 -14.750  -0.9198   0.03048   0.02467  -0.0942   0.8193   0.0133
 -14.500  -0.9090   0.02947   0.02359  -0.0934   0.8154   0.0134
 -14.250  -0.8969   0.02852   0.02259  -0.0926   0.8121   0.0136
 -14.000  -0.8844   0.02763   0.02165  -0.0917   0.8084   0.0137
 -13.750  -0.8720   0.02676   0.02071  -0.0908   0.8047   0.0138
 -13.500  -0.8592   0.02594   0.01983  -0.0898   0.8010   0.0139
 -13.250  -0.8457   0.02517   0.01901  -0.0889   0.7976   0.0141
 -13.000  -0.8307   0.02447   0.01827  -0.0881   0.7947   0.0144
 -12.750  -0.8172   0.02372   0.01746  -0.0871   0.7913   0.0145
 -12.500  -0.8031   0.02301   0.01670  -0.0861   0.7879   0.0146
 -12.250  -0.7870   0.02244   0.01608  -0.0852   0.7848   0.0149
 -11.750  -0.7562   0.02122   0.01475  -0.0833   0.7795   0.0153
 -11.500  -0.7403   0.02063   0.01412  -0.0824   0.7770   0.0154
 -11.250  -0.7244   0.02004   0.01349  -0.0814   0.7743   0.0155
 -11.000  -0.7073   0.01955   0.01296  -0.0805   0.7717   0.0156
 -10.750  -0.6920   0.01896   0.01233  -0.0794   0.7691   0.0158
 -10.500  -0.6766   0.01839   0.01173  -0.0782   0.7666   0.0164
 -10.250  -0.6594   0.01793   0.01124  -0.0772   0.7642   0.0167
 -10.000  -0.6418   0.01746   0.01075  -0.0763   0.7624   0.0170
  -9.750  -0.6236   0.01703   0.01030  -0.0754   0.7604   0.0173
  -9.500  -0.6054   0.01661   0.00986  -0.0745   0.7582   0.0178
  -9.250  -0.5871   0.01620   0.00943  -0.0735   0.7561   0.0181
  -9.000  -0.5686   0.01582   0.00902  -0.0726   0.7540   0.0186
  -8.750  -0.5497   0.01546   0.00862  -0.0717   0.7520   0.0188
  -8.500  -0.5316   0.01507   0.00821  -0.0707   0.7500   0.0192
  -8.000  -0.4943   0.01436   0.00748  -0.0687   0.7466   0.0208
  -7.750  -0.4748   0.01403   0.00715  -0.0678   0.7451   0.0218
  -7.500  -0.4550   0.01372   0.00683  -0.0670   0.7436   0.0224
  -7.250  -0.4358   0.01340   0.00651  -0.0660   0.7419   0.0234
  -7.000  -0.4167   0.01308   0.00619  -0.0650   0.7402   0.0249
  -6.750  -0.3970   0.01280   0.00590  -0.0641   0.7385   0.0261
  -6.500  -0.3774   0.01252   0.00562  -0.0631   0.7369   0.0277
  -6.250  -0.3582   0.01224   0.00533  -0.0620   0.7351   0.0292
  -6.000  -0.3388   0.01198   0.00506  -0.0609   0.7335   0.0313
  -5.750  -0.3196   0.01172   0.00480  -0.0598   0.7319   0.0338
  -5.500  -0.3003   0.01146   0.00455  -0.0587   0.7307   0.0370
  -5.250  -0.2820   0.01118   0.00430  -0.0573   0.7296   0.0426
  -5.000  -0.2648   0.01089   0.00406  -0.0558   0.7284   0.0515
  -4.750  -0.2524   0.01054   0.00381  -0.0533   0.7271   0.0717
  -4.500  -0.2416   0.01025   0.00361  -0.0505   0.7257   0.0946
  -4.250  -0.2299   0.00984   0.00338  -0.0478   0.7244   0.1372
  -4.000  -0.2158   0.00943   0.00315  -0.0457   0.7231   0.1835
  -3.750  -0.2023   0.00894   0.00290  -0.0435   0.7218   0.2428
  -3.500  -0.1877   0.00844   0.00265  -0.0415   0.7205   0.3078
  -3.250  -0.1747   0.00780   0.00235  -0.0392   0.7193   0.3948
  -3.000  -0.1647   0.00692   0.00195  -0.0365   0.7181   0.5172
  -2.750  -0.1492   0.00630   0.00180  -0.0345   0.7169   0.6423
  -2.500  -0.1213   0.00630   0.00183  -0.0347   0.7159   0.6639
  -2.250  -0.0925   0.00632   0.00184  -0.0351   0.7148   0.6742
  -2.000  -0.0637   0.00635   0.00186  -0.0356   0.7142   0.6835
  -1.750  -0.0348   0.00637   0.00190  -0.0360   0.7135   0.6911
  -1.500  -0.0057   0.00639   0.00193  -0.0364   0.7126   0.6960
  -1.250   0.0236   0.00641   0.00193  -0.0370   0.7117   0.6995
  -1.000   0.0529   0.00644   0.00194  -0.0375   0.7107   0.7026
  -0.750   0.0822   0.00644   0.00195  -0.0380   0.7099   0.7054
  -0.500   0.1115   0.00644   0.00195  -0.0386   0.7090   0.7070
  -0.250   0.1409   0.00644   0.00195  -0.0392   0.7082   0.7078
   0.000   0.1703   0.00644   0.00196  -0.0397   0.7074   0.7086
   0.250   0.1997   0.00644   0.00197  -0.0403   0.7065   0.7094
   0.500   0.2291   0.00645   0.00198  -0.0409   0.7057   0.7103
   0.750   0.2584   0.00646   0.00200  -0.0414   0.7045   0.7111
   1.000   0.2875   0.00647   0.00199  -0.0419   0.7024   0.7120
   1.250   0.3166   0.00649   0.00199  -0.0424   0.6992   0.7128
   1.500   0.3453   0.00649   0.00201  -0.0429   0.6966   0.7137
   1.750   0.3742   0.00649   0.00203  -0.0433   0.6943   0.7146
   2.000   0.4028   0.00648   0.00205  -0.0437   0.6910   0.7155
   2.250   0.4313   0.00648   0.00204  -0.0441   0.6868   0.7165
   2.500   0.4596   0.00651   0.00205  -0.0444   0.6821   0.7176
   2.750   0.4877   0.00650   0.00208  -0.0447   0.6773   0.7185
   3.000   0.5151   0.00651   0.00208  -0.0448   0.6691   0.7193
   3.250   0.5428   0.00653   0.00211  -0.0450   0.6619   0.7200
   3.500   0.5687   0.00655   0.00213  -0.0448   0.6483   0.7210
   3.750   0.5869   0.00673   0.00215  -0.0431   0.5962   0.7222
   4.000   0.5812   0.00760   0.00258  -0.0367   0.5005   0.7238
   4.250   0.5715   0.00840   0.00303  -0.0297   0.4229   0.7254
   4.500   0.5625   0.00908   0.00347  -0.0229   0.3649   0.7271
   4.750   0.5594   0.00985   0.00402  -0.0175   0.3124   0.7288
   5.000   0.5642   0.01050   0.00450  -0.0138   0.2737   0.7304
   5.250   0.5637   0.01138   0.00513  -0.0094   0.2178   0.7321
   5.500   0.5741   0.01197   0.00560  -0.0069   0.1880   0.7335
   5.750   0.5788   0.01281   0.00621  -0.0036   0.1409   0.7350
   6.000   0.5874   0.01355   0.00678  -0.0010   0.1040   0.7364
   6.250   0.5983   0.01423   0.00731   0.0012   0.0744   0.7377
   6.500   0.6130   0.01476   0.00778   0.0028   0.0582   0.7394
   6.750   0.6284   0.01527   0.00824   0.0043   0.0445   0.7410
   7.000   0.6453   0.01574   0.00868   0.0055   0.0365   0.7427
   7.250   0.6631   0.01618   0.00910   0.0066   0.0321   0.7445
   7.500   0.6811   0.01662   0.00954   0.0076   0.0290   0.7464
   7.750   0.6994   0.01704   0.00997   0.0085   0.0267   0.7484
   8.000   0.7177   0.01749   0.01041   0.0094   0.0248   0.7502
   8.250   0.7359   0.01794   0.01087   0.0103   0.0230   0.7520
   8.500   0.7538   0.01842   0.01135   0.0113   0.0217   0.7536
   8.750   0.7721   0.01888   0.01182   0.0121   0.0203   0.7552
   9.000   0.7898   0.01936   0.01231   0.0130   0.0188   0.7573
   9.250   0.8068   0.01989   0.01286   0.0140   0.0177   0.7595
   9.500   0.8246   0.02038   0.01338   0.0149   0.0169   0.7617
   9.750   0.8423   0.02089   0.01391   0.0157   0.0163   0.7639
  10.000   0.8592   0.02146   0.01449   0.0166   0.0153   0.7662
  10.250   0.8760   0.02204   0.01509   0.0175   0.0149   0.7685
  10.500   0.8920   0.02269   0.01575   0.0184   0.0142   0.7705
  10.750   0.9089   0.02329   0.01638   0.0193   0.0141   0.7726
  11.000   0.9254   0.02390   0.01703   0.0201   0.0138   0.7752
  11.250   0.9413   0.02456   0.01774   0.0210   0.0134   0.7779
  11.500   0.9573   0.02522   0.01844   0.0218   0.0129   0.7807
  11.750   0.9729   0.02593   0.01918   0.0227   0.0128   0.7835
  12.000   0.9880   0.02668   0.01997   0.0236   0.0125   0.7863
  12.250   1.0029   0.02747   0.02077   0.0244   0.0121   0.7888
  12.500   1.0169   0.02831   0.02166   0.0253   0.0119   0.7917
  12.750   1.0308   0.02916   0.02257   0.0262   0.0118   0.7949
  13.000   1.0426   0.03017   0.02363   0.0272   0.0115   0.7983
  13.250   1.0560   0.03110   0.02461   0.0281   0.0114   0.8016
  13.500   1.0698   0.03202   0.02558   0.0288   0.0114   0.8049
  13.750   1.0826   0.03303   0.02665   0.0296   0.0111   0.8080
  14.000   1.0954   0.03402   0.02770   0.0304   0.0110   0.8119
  14.250   1.1065   0.03517   0.02892   0.0312   0.0111   0.8161
  14.500   1.1175   0.03635   0.03017   0.0320   0.0108   0.8201
  14.750   1.1283   0.03759   0.03147   0.0327   0.0108   0.8240
  15.000   1.1399   0.03874   0.03269   0.0334   0.0105   0.8280
  15.250   1.1476   0.04026   0.03429   0.0342   0.0107   0.8325
  15.500   1.1590   0.04149   0.03559   0.0348   0.0104   0.8370
  15.750   1.1666   0.04309   0.03726   0.0354   0.0104   0.8412
  16.000   1.1748   0.04463   0.03889   0.0360   0.0104   0.8458
  16.250   1.1837   0.04614   0.04046   0.0365   0.0101   0.8512
  16.500   1.1926   0.04771   0.04211   0.0369   0.0101   0.8566
  16.750   1.1999   0.04943   0.04392   0.0373   0.0100   0.8620
  17.000   1.2031   0.05158   0.04618   0.0378   0.0099   0.8686
  17.250   1.2085   0.05358   0.04826   0.0381   0.0098   0.8753
  17.500   1.2121   0.05574   0.05053   0.0384   0.0098   0.8833
  18.000   1.2188   0.06029   0.05528   0.0387   0.0096   0.9039
  18.250   1.2200   0.06287   0.05798   0.0387   0.0095   0.9168
  18.500   1.2208   0.06562   0.06087   0.0385   0.0095   0.9330
  18.750   1.2245   0.06907   0.06447   0.0366   0.0094   0.9544
  19.000   1.2302   0.07331   0.06885   0.0331   0.0093   0.9716
  19.250   1.2270   0.07667   0.07230   0.0325   0.0093   1.0000
<< Back to NACA 66(3)-218 (naca663218-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(3)-218 (naca663218-il)