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N-12 (n12-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: N-12 (n12-il)
Reynolds number: 200,000
Max Cl/Cd: 42.87 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n12-il-200000-n5.txt
Download as CSV file: xf-n12-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-12                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6929   0.10942   0.10555  -0.0113   1.0000   0.0204
 -12.750  -0.8410   0.06856   0.06426  -0.0388   1.0000   0.0184
 -12.500  -0.8677   0.06168   0.05715  -0.0429   1.0000   0.0183
 -12.250  -0.8866   0.05697   0.05226  -0.0445   1.0000   0.0183
 -12.000  -0.9012   0.05341   0.04853  -0.0445   1.0000   0.0185
 -11.750  -0.9154   0.05028   0.04523  -0.0433   1.0000   0.0186
 -11.500  -0.9250   0.04796   0.04274  -0.0412   1.0000   0.0188
 -11.250  -0.9332   0.04594   0.04058  -0.0384   1.0000   0.0191
 -11.000  -0.9413   0.04412   0.03860  -0.0346   1.0000   0.0195
 -10.750  -0.9467   0.04225   0.03655  -0.0309   1.0000   0.0198
 -10.500  -0.9471   0.04042   0.03450  -0.0277   1.0000   0.0204
 -10.250  -0.9459   0.03862   0.03244  -0.0245   1.0000   0.0213
 -10.000  -0.9433   0.03680   0.03027  -0.0213   1.0000   0.0222
  -9.750  -0.9381   0.03537   0.02847  -0.0181   1.0000   0.0230
  -9.500  -0.9302   0.03333   0.02614  -0.0155   1.0000   0.0236
  -9.250  -0.9168   0.03157   0.02432  -0.0138   1.0000   0.0244
  -9.000  -0.9026   0.03029   0.02293  -0.0120   1.0000   0.0251
  -8.750  -0.8876   0.02921   0.02175  -0.0102   1.0000   0.0262
  -8.500  -0.8718   0.02813   0.02052  -0.0083   1.0000   0.0273
  -8.250  -0.8552   0.02698   0.01919  -0.0065   1.0000   0.0283
  -8.000  -0.8376   0.02592   0.01795  -0.0048   1.0000   0.0292
  -7.750  -0.8197   0.02522   0.01705  -0.0031   1.0000   0.0302
  -7.500  -0.8014   0.02391   0.01562  -0.0015   1.0000   0.0313
  -7.250  -0.7829   0.02249   0.01419  -0.0001   1.0000   0.0323
  -7.000  -0.7646   0.02149   0.01317   0.0014   1.0000   0.0331
  -6.750  -0.7467   0.02065   0.01231   0.0031   1.0000   0.0342
  -6.500  -0.7287   0.01991   0.01152   0.0048   1.0000   0.0354
  -6.250  -0.7109   0.01922   0.01078   0.0066   1.0000   0.0365
  -6.000  -0.6932   0.01857   0.01009   0.0085   1.0000   0.0372
  -5.750  -0.6759   0.01796   0.00943   0.0104   1.0000   0.0379
  -5.500  -0.6587   0.01741   0.00884   0.0124   1.0000   0.0385
  -5.250  -0.6413   0.01694   0.00831   0.0143   1.0000   0.0392
  -5.000  -0.6237   0.01655   0.00787   0.0162   1.0000   0.0400
  -4.750  -0.6079   0.01603   0.00731   0.0184   1.0000   0.0410
  -4.500  -0.5838   0.01554   0.00676   0.0189   0.9983   0.0421
  -4.250  -0.5493   0.01512   0.00627   0.0172   0.9940   0.0434
  -4.000  -0.5162   0.01472   0.00582   0.0159   0.9890   0.0450
  -3.750  -0.4817   0.01439   0.00545   0.0143   0.9847   0.0469
  -3.500  -0.4506   0.01408   0.00508   0.0134   0.9783   0.0491
  -3.250  -0.4181   0.01374   0.00475   0.0123   0.9728   0.0554
  -3.000  -0.3897   0.01317   0.00448   0.0118   0.9655   0.1092
  -2.750  -0.3597   0.01283   0.00424   0.0112   0.9584   0.1346
  -2.500  -0.3288   0.01242   0.00399   0.0104   0.9516   0.1688
  -2.250  -0.3024   0.01175   0.00371   0.0103   0.9428   0.2503
  -2.000  -0.2707   0.01111   0.00351   0.0093   0.9351   0.3566
  -1.750  -0.2377   0.01068   0.00329   0.0082   0.9239   0.4144
  -1.500  -0.2014   0.01015   0.00305   0.0064   0.9119   0.4757
  -1.250  -0.1685   0.00950   0.00292   0.0054   0.8999   0.5874
  -1.000  -0.1342   0.00905   0.00292   0.0045   0.8874   0.6978
  -0.750  -0.0950   0.00885   0.00302   0.0027   0.8734   0.7770
  -0.500  -0.0563   0.00882   0.00304   0.0009   0.8550   0.8130
  -0.250  -0.0192   0.00883   0.00302  -0.0007   0.8332   0.8342
   0.000   0.0155   0.00887   0.00302  -0.0018   0.8079   0.8535
   0.250   0.0498   0.00894   0.00301  -0.0027   0.7769   0.8704
   0.500   0.0855   0.00905   0.00304  -0.0040   0.7439   0.8853
   0.750   0.1223   0.00920   0.00308  -0.0055   0.7106   0.8967
   1.000   0.1542   0.00936   0.00311  -0.0061   0.6744   0.9062
   1.250   0.1903   0.00957   0.00318  -0.0076   0.6375   0.9127
   1.500   0.2222   0.00979   0.00326  -0.0083   0.6024   0.9212
   1.750   0.2580   0.01006   0.00339  -0.0098   0.5606   0.9271
   2.000   0.2856   0.01039   0.00349  -0.0097   0.5078   0.9355
   2.250   0.3170   0.01082   0.00364  -0.0104   0.4378   0.9406
   2.500   0.3413   0.01131   0.00379  -0.0098   0.3680   0.9492
   3.000   0.4022   0.01200   0.00420  -0.0112   0.3004   0.9615
   3.250   0.4360   0.01226   0.00441  -0.0126   0.2803   0.9663
   3.500   0.4659   0.01255   0.00462  -0.0132   0.2563   0.9728
   3.750   0.4991   0.01284   0.00484  -0.0145   0.2283   0.9777
   4.000   0.5274   0.01351   0.00507  -0.0152   0.1327   0.9842
   4.250   0.5601   0.01411   0.00550  -0.0166   0.1038   0.9887
   4.500   0.5925   0.01449   0.00588  -0.0179   0.0786   0.9933
   4.750   0.6246   0.01492   0.00620  -0.0191   0.0598   0.9971
   5.000   0.6549   0.01534   0.00661  -0.0199   0.0535   1.0000
   5.250   0.6722   0.01568   0.00702  -0.0180   0.0506   1.0000
   5.500   0.6888   0.01607   0.00744  -0.0159   0.0479   1.0000
   5.750   0.7042   0.01660   0.00799  -0.0137   0.0453   1.0000
   6.000   0.7202   0.01708   0.00853  -0.0115   0.0439   1.0000
   6.250   0.7364   0.01758   0.00912  -0.0094   0.0427   1.0000
   6.500   0.7527   0.01811   0.00972  -0.0073   0.0414   1.0000
   6.750   0.7691   0.01867   0.01034  -0.0052   0.0397   1.0000
   7.000   0.7852   0.01929   0.01100  -0.0031   0.0380   1.0000
   7.250   0.8006   0.02003   0.01177  -0.0010   0.0366   1.0000
   7.500   0.8141   0.02109   0.01285   0.0014   0.0350   1.0000
   7.750   0.8305   0.02190   0.01376   0.0034   0.0338   1.0000
   8.000   0.8476   0.02260   0.01458   0.0052   0.0325   1.0000
   8.250   0.8642   0.02345   0.01554   0.0071   0.0311   1.0000
   8.500   0.8804   0.02430   0.01648   0.0090   0.0296   1.0000
   8.750   0.8959   0.02513   0.01736   0.0109   0.0282   1.0000
   9.000   0.9105   0.02620   0.01847   0.0128   0.0270   1.0000
   9.250   0.9242   0.02780   0.02019   0.0147   0.0259   1.0000
   9.500   0.9385   0.02881   0.02142   0.0169   0.0249   1.0000
   9.750   0.9516   0.02994   0.02276   0.0190   0.0238   1.0000
  10.000   0.9632   0.03098   0.02398   0.0213   0.0225   1.0000
  10.250   0.9740   0.03204   0.02517   0.0236   0.0216   1.0000
  10.500   0.9836   0.03317   0.02640   0.0259   0.0209   1.0000
  10.750   0.9916   0.03438   0.02769   0.0283   0.0203   1.0000
  11.000   0.9962   0.03610   0.02952   0.0309   0.0197   1.0000
  11.250   0.9938   0.03780   0.03148   0.0347   0.0193   1.0000
  11.500   0.9879   0.03980   0.03376   0.0386   0.0189   1.0000
  11.750   0.9802   0.04193   0.03618   0.0419   0.0183   1.0000
  12.000   0.9702   0.04454   0.03904   0.0444   0.0180   1.0000
  12.250   0.9572   0.04760   0.04235   0.0461   0.0177   1.0000
  12.500   0.9477   0.05042   0.04536   0.0467   0.0170   1.0000
  12.750   0.9281   0.05508   0.05027   0.0460   0.0171   1.0000
  13.000   0.9141   0.05948   0.05485   0.0442   0.0167   1.0000
  13.250   0.8828   0.06748   0.06311   0.0395   0.0172   1.0000
  13.500   0.8489   0.07736   0.07322   0.0326   0.0174   1.0000
  13.750   0.8041   0.09126   0.08729   0.0231   0.0182   1.0000
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