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NACA 67 (naca671215-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 200,000
Max Cl/Cd: 33.39 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca671215-il-200000-n5.txt
Download as CSV file: xf-naca671215-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 67                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.6392   0.06077   0.05605  -0.1148   0.9669   0.0216
 -13.750  -0.6580   0.05539   0.05039  -0.1171   0.9642   0.0216
 -13.500  -0.6729   0.05116   0.04589  -0.1177   0.9607   0.0217
 -13.250  -0.6815   0.04812   0.04263  -0.1172   0.9566   0.0219
 -13.000  -0.6871   0.04526   0.03952  -0.1165   0.9532   0.0221
 -12.750  -0.6889   0.04261   0.03660  -0.1157   0.9504   0.0224
 -12.500  -0.6932   0.04038   0.03411  -0.1134   0.9460   0.0225
 -12.250  -0.6928   0.03845   0.03194  -0.1114   0.9421   0.0228
 -12.000  -0.6888   0.03655   0.02978  -0.1096   0.9390   0.0232
 -11.750  -0.6811   0.03471   0.02766  -0.1081   0.9365   0.0237
 -11.500  -0.6750   0.03319   0.02590  -0.1057   0.9327   0.0241
 -11.250  -0.6646   0.03175   0.02419  -0.1039   0.9295   0.0246
 -11.000  -0.6514   0.03046   0.02260  -0.1023   0.9270   0.0253
 -10.750  -0.6344   0.02945   0.02155  -0.1015   0.9250   0.0260
 -10.500  -0.6175   0.02869   0.02072  -0.1006   0.9231   0.0267
 -10.250  -0.5985   0.02785   0.01978  -0.0999   0.9216   0.0276
 -10.000  -0.5809   0.02704   0.01885  -0.0988   0.9195   0.0285
  -9.750  -0.5618   0.02621   0.01787  -0.0978   0.9174   0.0296
  -9.500  -0.5413   0.02544   0.01695  -0.0971   0.9155   0.0306
  -9.250  -0.5221   0.02467   0.01617  -0.0962   0.9136   0.0317
  -9.000  -0.5035   0.02409   0.01557  -0.0952   0.9116   0.0328
  -8.750  -0.4838   0.02353   0.01495  -0.0944   0.9098   0.0343
  -8.500  -0.4630   0.02301   0.01433  -0.0936   0.9082   0.0365
  -8.250  -0.4431   0.02242   0.01369  -0.0928   0.9070   0.0382
  -8.000  -0.4233   0.02198   0.01325  -0.0920   0.9058   0.0406
  -7.750  -0.4088   0.02173   0.01295  -0.0900   0.9035   0.0428
  -7.500  -0.3939   0.02149   0.01264  -0.0881   0.9012   0.0449
  -7.250  -0.3806   0.02111   0.01229  -0.0860   0.8989   0.0476
  -7.000  -0.3650   0.02082   0.01198  -0.0843   0.8968   0.0505
  -6.750  -0.3479   0.02051   0.01161  -0.0827   0.8949   0.0533
  -6.500  -0.3317   0.02011   0.01119  -0.0810   0.8932   0.0560
  -6.250  -0.3147   0.01976   0.01085  -0.0795   0.8918   0.0601
  -6.000  -0.2962   0.01948   0.01050  -0.0781   0.8907   0.0642
  -5.750  -0.2855   0.01929   0.01034  -0.0753   0.8886   0.0690
  -5.500  -0.2872   0.01946   0.01052  -0.0700   0.8845   0.0733
  -5.250  -0.2805   0.01937   0.01045  -0.0662   0.8813   0.0805
  -5.000  -0.2715   0.01920   0.01034  -0.0630   0.8790   0.0943
  -4.750  -0.2613   0.01895   0.01019  -0.0599   0.8772   0.1184
  -4.500  -0.2516   0.01859   0.01002  -0.0568   0.8756   0.1582
  -4.250  -0.2411   0.01810   0.00979  -0.0539   0.8742   0.2180
  -4.000  -0.2778   0.01889   0.01056  -0.0413   0.8657   0.2168
  -3.750  -0.2762   0.01837   0.01037  -0.0366   0.8628   0.2925
  -3.500  -0.2765   0.01761   0.01009  -0.0316   0.8606   0.3975
  -3.250  -0.2782   0.01663   0.00978  -0.0260   0.8588   0.5394
  -2.750  -0.2750   0.01791   0.01203  -0.0138   0.8495   0.7472
  -2.500  -0.2610   0.01799   0.01204  -0.0110   0.8471   0.7744
  -2.250  -0.2438   0.01819   0.01217  -0.0087   0.8455   0.7981
  -2.000  -0.2090   0.01945   0.01345  -0.0084   0.8448   0.8218
  -1.750  -0.1672   0.02106   0.01505  -0.0092   0.8445   0.8430
  -1.500  -0.1243   0.02172   0.01566  -0.0116   0.8442   0.8489
  -1.250  -0.0901   0.02183   0.01570  -0.0130   0.8436   0.8510
  -1.000  -0.1372   0.02188   0.01576   0.0013   0.8329   0.8624
  -0.750  -0.1077   0.02191   0.01574   0.0007   0.8314   0.8636
  -0.500  -0.0767   0.02189   0.01567  -0.0001   0.8302   0.8649
  -0.250  -0.0460   0.02185   0.01560  -0.0009   0.8291   0.8663
   0.000  -0.0155   0.02179   0.01551  -0.0017   0.8281   0.8678
   0.500  -0.0208   0.02158   0.01525   0.0093   0.8157   0.8781
   0.750   0.0103   0.02152   0.01517   0.0084   0.8142   0.8790
   1.000   0.0422   0.02141   0.01505   0.0074   0.8130   0.8798
   1.250   0.0749   0.02128   0.01492   0.0062   0.8119   0.8805
   1.750   0.0974   0.02141   0.01507   0.0119   0.7997   0.8852
   2.000   0.1281   0.02121   0.01488   0.0112   0.7979   0.8863
   2.250   0.1609   0.02097   0.01466   0.0101   0.7965   0.8874
   2.750   0.1872   0.02071   0.01444   0.0150   0.7834   0.8928
   3.000   0.2205   0.02036   0.01412   0.0139   0.7816   0.8937
   3.500   0.2620   0.02001   0.01386   0.0164   0.7681   0.8964
   3.750   0.2962   0.01949   0.01339   0.0155   0.7639   0.8972
   4.000   0.3112   0.01933   0.01328   0.0178   0.7534   0.8990
   4.500   0.3466   0.01869   0.01275   0.0217   0.7286   0.9025
   5.000   0.3855   0.01781   0.01195   0.0252   0.6883   0.9062
   5.250   0.4932   0.01477   0.00834   0.0139   0.5691   0.9016
   5.500   0.4988   0.01528   0.00832   0.0180   0.4751   0.9040
   5.750   0.4957   0.01597   0.00865   0.0231   0.4043   0.9078
   6.000   0.4960   0.01670   0.00905   0.0274   0.3374   0.9106
   6.250   0.5006   0.01744   0.00949   0.0310   0.2749   0.9126
   6.500   0.5086   0.01813   0.00993   0.0337   0.2189   0.9147
   6.750   0.5186   0.01883   0.01037   0.0361   0.1661   0.9168
   7.000   0.5312   0.01948   0.01081   0.0380   0.1252   0.9190
   7.250   0.5456   0.02005   0.01125   0.0396   0.0980   0.9213
   7.500   0.5612   0.02058   0.01170   0.0411   0.0810   0.9239
   7.750   0.5774   0.02109   0.01218   0.0425   0.0704   0.9260
   8.000   0.5936   0.02164   0.01271   0.0438   0.0635   0.9278
   8.250   0.6112   0.02212   0.01324   0.0449   0.0587   0.9299
   8.500   0.6272   0.02270   0.01384   0.0462   0.0549   0.9322
   8.750   0.6435   0.02328   0.01445   0.0475   0.0513   0.9346
   9.000   0.6607   0.02380   0.01503   0.0485   0.0476   0.9371
   9.250   0.6757   0.02452   0.01572   0.0497   0.0442   0.9396
   9.500   0.6953   0.02504   0.01633   0.0503   0.0413   0.9416
   9.750   0.7132   0.02567   0.01703   0.0511   0.0389   0.9441
  10.000   0.7288   0.02644   0.01782   0.0521   0.0370   0.9470
  10.250   0.7459   0.02711   0.01857   0.0530   0.0346   0.9504
  10.500   0.7642   0.02782   0.01936   0.0536   0.0326   0.9533
  10.750   0.7822   0.02863   0.02021   0.0539   0.0307   0.9561
  11.000   0.7997   0.02956   0.02121   0.0544   0.0293   0.9591
  11.250   0.8179   0.03048   0.02224   0.0549   0.0279   0.9622
  11.500   0.8369   0.03145   0.02331   0.0550   0.0264   0.9650
  11.750   0.8564   0.03250   0.02443   0.0548   0.0255   0.9676
  12.000   0.8743   0.03377   0.02572   0.0548   0.0245   0.9706
  12.250   0.8944   0.03499   0.02711   0.0546   0.0239   0.9737
  12.500   0.9142   0.03639   0.02870   0.0544   0.0230   0.9766
  12.750   0.9328   0.03784   0.03031   0.0541   0.0223   0.9802
  13.250   0.9634   0.04071   0.03345   0.0538   0.0210   0.9990
  13.500   0.9713   0.04205   0.03485   0.0550   0.0206   1.0000
  13.750   0.9785   0.04362   0.03649   0.0561   0.0202   1.0000
  14.000   0.9838   0.04547   0.03849   0.0573   0.0199   1.0000
  14.250   0.9868   0.04762   0.04088   0.0585   0.0197   1.0000
  14.500   0.9853   0.05021   0.04375   0.0598   0.0192   1.0000
  14.750   0.9833   0.05285   0.04662   0.0608   0.0191   1.0000
  15.000   0.9769   0.05599   0.05001   0.0618   0.0188   1.0000
  15.250   0.9688   0.05941   0.05367   0.0624   0.0187   1.0000
  15.500   0.9570   0.06333   0.05782   0.0626   0.0184   1.0000
  15.750   0.9416   0.06799   0.06273   0.0622   0.0184   1.0000
  16.000   0.9242   0.07320   0.06817   0.0611   0.0183   1.0000
  16.250   0.9030   0.07940   0.07461   0.0589   0.0184   1.0000
  16.500   0.8749   0.08740   0.08286   0.0553   0.0184   1.0000
  16.750   0.8395   0.09780   0.09354   0.0494   0.0185   1.0000
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