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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 100,000
Max Cl/Cd: 42.15 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212-il-100000-n5.txt
Download as CSV file: xf-naca651212-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4366   0.09476   0.08988  -0.0369   1.0000   0.0352
 -11.000  -0.4455   0.08857   0.08372  -0.0397   1.0000   0.0351
 -10.750  -0.4578   0.08140   0.07657  -0.0431   1.0000   0.0346
 -10.250  -0.6354   0.06697   0.06142  -0.0553   1.0000   0.0289
 -10.000  -0.6511   0.06350   0.05785  -0.0548   1.0000   0.0288
  -9.750  -0.6661   0.06048   0.05472  -0.0530   1.0000   0.0287
  -9.500  -0.6791   0.05734   0.05137  -0.0510   1.0000   0.0288
  -9.250  -0.6902   0.05431   0.04811  -0.0485   1.0000   0.0291
  -9.000  -0.6958   0.05109   0.04475  -0.0463   1.0000   0.0295
  -8.750  -0.6978   0.04865   0.04219  -0.0438   1.0000   0.0300
  -8.500  -0.6958   0.04691   0.04041  -0.0414   1.0000   0.0308
  -8.250  -0.6966   0.04515   0.03850  -0.0383   1.0000   0.0314
  -8.000  -0.6992   0.04313   0.03627  -0.0347   1.0000   0.0318
  -7.750  -0.6858   0.04008   0.03281  -0.0342   0.9953   0.0320
  -7.500  -0.6608   0.03688   0.02913  -0.0355   0.9879   0.0324
  -7.250  -0.6333   0.03414   0.02596  -0.0367   0.9814   0.0331
  -7.000  -0.6031   0.03188   0.02331  -0.0381   0.9758   0.0345
  -6.750  -0.5732   0.03008   0.02110  -0.0391   0.9695   0.0365
  -6.500  -0.5399   0.02823   0.01889  -0.0405   0.9648   0.0376
  -6.250  -0.5070   0.02668   0.01707  -0.0417   0.9599   0.0384
  -6.000  -0.4761   0.02479   0.01517  -0.0427   0.9546   0.0397
  -5.750  -0.4432   0.02351   0.01387  -0.0442   0.9502   0.0422
  -5.500  -0.4154   0.02262   0.01292  -0.0446   0.9430   0.0456
  -5.250  -0.3850   0.02165   0.01187  -0.0454   0.9373   0.0482
  -5.000  -0.3589   0.02074   0.01089  -0.0455   0.9303   0.0505
  -4.750  -0.3329   0.01992   0.01004  -0.0457   0.9233   0.0547
  -4.500  -0.3055   0.01935   0.00935  -0.0460   0.9170   0.0617
  -4.250  -0.2816   0.01865   0.00865  -0.0457   0.9092   0.0705
  -4.000  -0.2550   0.01785   0.00796  -0.0459   0.9035   0.0949
  -3.750  -0.2417   0.01614   0.00724  -0.0446   0.8945   0.2832
  -3.500  -0.2271   0.01499   0.00738  -0.0422   0.8883   0.5653
  -3.250  -0.2070   0.01518   0.00775  -0.0399   0.8805   0.6528
  -3.000  -0.1848   0.01578   0.00847  -0.0369   0.8755   0.7158
  -2.750  -0.1655   0.01638   0.00907  -0.0336   0.8682   0.7487
  -2.500  -0.1391   0.01647   0.00903  -0.0329   0.8627   0.7615
  -2.250  -0.1116   0.01642   0.00885  -0.0328   0.8575   0.7685
  -2.000  -0.0864   0.01636   0.00866  -0.0325   0.8507   0.7752
  -1.750  -0.0576   0.01630   0.00850  -0.0325   0.8461   0.7805
  -1.500  -0.0326   0.01624   0.00833  -0.0324   0.8397   0.7880
  -1.250  -0.0058   0.01623   0.00826  -0.0321   0.8342   0.7926
  -1.000   0.0228   0.01617   0.00811  -0.0322   0.8301   0.7985
  -0.750   0.0469   0.01617   0.00807  -0.0318   0.8232   0.8050
  -0.500   0.0738   0.01617   0.00803  -0.0316   0.8181   0.8102
  -0.250   0.1024   0.01610   0.00791  -0.0319   0.8144   0.8168
   0.000   0.1257   0.01618   0.00799  -0.0312   0.8073   0.8224
   0.250   0.1527   0.01617   0.00797  -0.0311   0.8025   0.8286
   0.500   0.1803   0.01616   0.00794  -0.0311   0.7984   0.8351
   0.750   0.2039   0.01626   0.00808  -0.0305   0.7917   0.8409
   1.000   0.2309   0.01626   0.00808  -0.0305   0.7870   0.8484
   1.250   0.2578   0.01629   0.00816  -0.0303   0.7827   0.8539
   1.500   0.2817   0.01640   0.00832  -0.0298   0.7761   0.8615
   1.750   0.3091   0.01642   0.00839  -0.0297   0.7717   0.8677
   2.000   0.3348   0.01650   0.00854  -0.0294   0.7667   0.8753
   2.250   0.3591   0.01662   0.00875  -0.0289   0.7605   0.8827
   2.500   0.3868   0.01663   0.00884  -0.0289   0.7561   0.8904
   2.750   0.4118   0.01676   0.00908  -0.0285   0.7500   0.8982
   3.000   0.4371   0.01684   0.00928  -0.0282   0.7439   0.9075
   3.250   0.4685   0.01678   0.00932  -0.0286   0.7392   0.9144
   3.500   0.4921   0.01690   0.00959  -0.0280   0.7299   0.9245
   3.750   0.5238   0.01679   0.00964  -0.0285   0.7227   0.9323
   4.000   0.5530   0.01645   0.00942  -0.0281   0.7052   0.9411
   4.250   0.5805   0.01549   0.00840  -0.0262   0.6595   0.9506
   4.500   0.6086   0.01501   0.00782  -0.0252   0.5927   0.9597
   4.750   0.6361   0.01509   0.00756  -0.0248   0.4787   0.9699
   5.000   0.6469   0.01714   0.00813  -0.0232   0.2256   0.9867
   5.250   0.6536   0.01891   0.00905  -0.0211   0.0965   1.0000
   5.500   0.6634   0.01980   0.00975  -0.0186   0.0715   1.0000
   5.750   0.6784   0.02062   0.01056  -0.0169   0.0616   1.0000
   6.250   0.7116   0.02229   0.01227  -0.0142   0.0495   1.0000
   6.500   0.7283   0.02320   0.01322  -0.0129   0.0463   1.0000
   6.750   0.7431   0.02440   0.01440  -0.0114   0.0439   1.0000
   7.000   0.7620   0.02547   0.01555  -0.0103   0.0419   1.0000
   7.250   0.7829   0.02652   0.01669  -0.0096   0.0393   1.0000
   7.500   0.8046   0.02767   0.01788  -0.0090   0.0369   1.0000
   7.750   0.8284   0.02906   0.01931  -0.0088   0.0355   1.0000
   8.000   0.8544   0.03078   0.02106  -0.0089   0.0342   1.0000
   8.250   0.8840   0.03321   0.02355  -0.0095   0.0333   1.0000
   8.500   0.9088   0.03510   0.02572  -0.0092   0.0327   1.0000
   8.750   0.9303   0.03700   0.02794  -0.0086   0.0318   1.0000
   9.000   0.9484   0.03898   0.03027  -0.0076   0.0304   1.0000
   9.250   0.9641   0.04122   0.03287  -0.0064   0.0294   1.0000
   9.500   0.9769   0.04385   0.03585  -0.0051   0.0290   1.0000
   9.750   0.9857   0.04663   0.03898  -0.0034   0.0286   1.0000
  10.000   0.9902   0.04958   0.04229  -0.0014   0.0283   1.0000
  10.250   0.9901   0.05264   0.04569   0.0008   0.0282   1.0000
  10.500   0.9837   0.05567   0.04903   0.0036   0.0281   1.0000
  10.750   0.9728   0.05885   0.05249   0.0062   0.0281   1.0000
  11.000   0.9588   0.06230   0.05620   0.0083   0.0282   1.0000
  11.250   0.9421   0.06610   0.06025   0.0097   0.0283   1.0000
  11.500   0.9230   0.07037   0.06474   0.0101   0.0284   1.0000
  11.750   0.9013   0.07531   0.06989   0.0094   0.0285   1.0000
  12.000   0.8775   0.08110   0.07587   0.0075   0.0287   1.0000
  12.250   0.8513   0.08811   0.08305   0.0040   0.0290   1.0000
  12.500   0.8242   0.09662   0.09168  -0.0012   0.0295   1.0000
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