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N-22 (n22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: N-22 (n22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.79 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n22-il-1000000-n5.txt
Download as CSV file: xf-n22-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-22                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.2106   0.03148   0.02825  -0.1017   0.9999   0.0157
 -17.500  -1.2048   0.02967   0.02630  -0.1010   0.9999   0.0160
 -17.250  -1.1945   0.02818   0.02468  -0.1002   0.9999   0.0163
 -17.000  -1.1819   0.02688   0.02329  -0.0992   0.9999   0.0166
 -16.750  -1.1669   0.02586   0.02222  -0.0982   0.9999   0.0171
 -16.500  -1.1512   0.02501   0.02132  -0.0968   0.9999   0.0175
 -16.250  -1.1364   0.02426   0.02051  -0.0952   0.9999   0.0180
 -16.000  -1.1117   0.02345   0.01963  -0.0954   0.9980   0.0185
 -15.750  -1.0848   0.02262   0.01870  -0.0959   0.9959   0.0190
 -15.500  -1.0571   0.02181   0.01780  -0.0965   0.9941   0.0194
 -15.250  -1.0307   0.02108   0.01697  -0.0968   0.9911   0.0197
 -15.000  -1.0044   0.02029   0.01610  -0.0970   0.9878   0.0200
 -14.750  -0.9764   0.01962   0.01539  -0.0975   0.9849   0.0205
 -14.500  -0.9486   0.01910   0.01482  -0.0977   0.9817   0.0209
 -14.250  -0.9217   0.01864   0.01432  -0.0976   0.9773   0.0214
 -14.000  -0.8942   0.01817   0.01379  -0.0977   0.9733   0.0219
 -13.750  -0.8681   0.01768   0.01324  -0.0974   0.9689   0.0223
 -13.500  -0.8427   0.01721   0.01270  -0.0970   0.9633   0.0227
 -13.250  -0.8168   0.01679   0.01219  -0.0966   0.9584   0.0231
 -13.000  -0.7915   0.01639   0.01173  -0.0960   0.9526   0.0234
 -12.750  -0.7662   0.01600   0.01126  -0.0954   0.9466   0.0236
 -12.500  -0.7417   0.01544   0.01062  -0.0948   0.9408   0.0240
 -12.250  -0.7167   0.01495   0.01007  -0.0942   0.9340   0.0245
 -12.000  -0.6912   0.01458   0.00965  -0.0936   0.9277   0.0250
 -11.750  -0.6648   0.01425   0.00928  -0.0932   0.9205   0.0254
 -11.500  -0.6387   0.01394   0.00891  -0.0927   0.9131   0.0258
 -11.250  -0.6122   0.01360   0.00851  -0.0923   0.9053   0.0262
 -11.000  -0.5858   0.01329   0.00812  -0.0918   0.8968   0.0266
 -10.750  -0.5589   0.01298   0.00774  -0.0914   0.8881   0.0271
 -10.500  -0.5324   0.01266   0.00734  -0.0910   0.8787   0.0274
 -10.250  -0.5053   0.01236   0.00696  -0.0906   0.8688   0.0277
 -10.000  -0.4782   0.01209   0.00660  -0.0902   0.8588   0.0279
  -9.500  -0.4241   0.01145   0.00580  -0.0896   0.8374   0.0288
  -9.250  -0.3968   0.01114   0.00542  -0.0893   0.8270   0.0293
  -8.750  -0.3415   0.01067   0.00483  -0.0888   0.8051   0.0302
  -8.500  -0.3137   0.01047   0.00457  -0.0886   0.7945   0.0307
  -8.000  -0.2576   0.01011   0.00408  -0.0882   0.7730   0.0316
  -7.750  -0.2295   0.00995   0.00385  -0.0880   0.7625   0.0321
  -7.500  -0.2014   0.00981   0.00364  -0.0879   0.7514   0.0327
  -7.250  -0.1730   0.00968   0.00345  -0.0878   0.7407   0.0332
  -7.000  -0.1448   0.00952   0.00322  -0.0876   0.7292   0.0338
  -6.750  -0.1168   0.00937   0.00301  -0.0875   0.7158   0.0348
  -6.500  -0.0885   0.00925   0.00284  -0.0874   0.7030   0.0358
  -6.250  -0.0599   0.00913   0.00269  -0.0874   0.6930   0.0368
  -6.000  -0.0314   0.00903   0.00254  -0.0873   0.6841   0.0379
  -5.750  -0.0027   0.00893   0.00241  -0.0873   0.6754   0.0389
  -5.500   0.0259   0.00883   0.00227  -0.0873   0.6667   0.0405
  -5.250   0.0546   0.00873   0.00215  -0.0873   0.6570   0.0428
  -5.000   0.0832   0.00865   0.00205  -0.0873   0.6483   0.0452
  -4.750   0.1120   0.00858   0.00195  -0.0873   0.6390   0.0480
  -4.500   0.1406   0.00850   0.00186  -0.0873   0.6293   0.0520
  -4.250   0.1692   0.00846   0.00178  -0.0873   0.6183   0.0556
  -4.000   0.1978   0.00839   0.00170  -0.0874   0.6072   0.0619
  -3.750   0.2264   0.00832   0.00164  -0.0874   0.5971   0.0707
  -3.500   0.2548   0.00826   0.00159  -0.0875   0.5859   0.0837
  -3.250   0.2832   0.00822   0.00156  -0.0875   0.5729   0.0974
  -3.000   0.3116   0.00820   0.00153  -0.0876   0.5593   0.1105
  -2.750   0.3400   0.00819   0.00151  -0.0877   0.5461   0.1236
  -2.500   0.3684   0.00819   0.00151  -0.0877   0.5335   0.1361
  -2.250   0.3967   0.00820   0.00151  -0.0878   0.5204   0.1511
  -2.000   0.4248   0.00819   0.00152  -0.0878   0.5061   0.1745
  -1.500   0.4807   0.00817   0.00157  -0.0880   0.4756   0.2384
  -1.250   0.5086   0.00812   0.00161  -0.0881   0.4618   0.2899
  -1.000   0.5364   0.00802   0.00166  -0.0882   0.4492   0.3632
  -0.750   0.5641   0.00797   0.00172  -0.0883   0.4372   0.4236
  -0.500   0.5917   0.00792   0.00179  -0.0884   0.4251   0.4873
  -0.250   0.6191   0.00783   0.00188  -0.0884   0.4127   0.5704
   0.000   0.6463   0.00776   0.00197  -0.0884   0.4013   0.6465
   0.250   0.6734   0.00772   0.00206  -0.0883   0.3914   0.7123
   0.500   0.6989   0.00757   0.00217  -0.0879   0.3823   0.8101
   0.750   0.7213   0.00737   0.00228  -0.0864   0.3745   0.9526
   1.000   0.7586   0.00753   0.00237  -0.0886   0.3610   1.0001
   1.250   0.7852   0.00774   0.00248  -0.0885   0.3442   1.0001
   1.500   0.8118   0.00795   0.00260  -0.0884   0.3291   1.0001
   1.750   0.8390   0.00811   0.00270  -0.0884   0.3192   1.0001
   2.000   0.8661   0.00827   0.00282  -0.0884   0.3118   1.0001
   2.250   0.8934   0.00841   0.00293  -0.0884   0.3046   1.0001
   2.500   0.9203   0.00859   0.00306  -0.0884   0.2973   1.0001
   2.750   0.9477   0.00873   0.00318  -0.0884   0.2915   1.0001
   3.000   0.9746   0.00890   0.00332  -0.0884   0.2851   1.0001
   3.250   1.0017   0.00905   0.00346  -0.0885   0.2796   1.0001
   3.500   1.0286   0.00921   0.00360  -0.0885   0.2731   1.0001
   3.750   1.0550   0.00941   0.00377  -0.0884   0.2662   1.0001
   4.000   1.0816   0.00959   0.00393  -0.0884   0.2581   1.0001
   4.250   1.1076   0.00982   0.00411  -0.0883   0.2486   1.0001
   4.500   1.1331   0.01008   0.00432  -0.0882   0.2375   1.0001
   4.750   1.1588   0.01032   0.00452  -0.0881   0.2265   1.0001
   5.000   1.1836   0.01061   0.00476  -0.0878   0.2133   1.0001
   5.250   1.2075   0.01098   0.00505  -0.0875   0.1966   1.0001
   5.500   1.2299   0.01146   0.00540  -0.0869   0.1760   1.0001
   5.750   1.2521   0.01194   0.00577  -0.0863   0.1577   1.0001
   6.000   1.2746   0.01237   0.00613  -0.0857   0.1442   1.0001
   6.250   1.2974   0.01276   0.00648  -0.0852   0.1344   1.0001
   6.500   1.3200   0.01315   0.00682  -0.0847   0.1257   1.0001
   6.750   1.3429   0.01350   0.00716  -0.0842   0.1190   1.0001
   7.250   1.3865   0.01429   0.00790  -0.0829   0.1048   1.0001
   7.500   1.4073   0.01473   0.00830  -0.0821   0.0987   1.0001
   7.750   1.4286   0.01511   0.00868  -0.0814   0.0935   1.0001
   8.000   1.4477   0.01558   0.00913  -0.0804   0.0870   1.0001
   8.250   1.4666   0.01601   0.00956  -0.0793   0.0816   1.0001
   8.500   1.4813   0.01657   0.01008  -0.0775   0.0741   1.0001
   8.750   1.4971   0.01710   0.01060  -0.0759   0.0673   1.0001
   9.000   1.5070   0.01799   0.01139  -0.0736   0.0534   1.0001
   9.250   1.5038   0.01970   0.01292  -0.0696   0.0277   1.0001
   9.500   1.5122   0.02077   0.01397  -0.0674   0.0205   1.0001
   9.750   1.5233   0.02171   0.01493  -0.0657   0.0172   1.0001
  10.000   1.5347   0.02266   0.01590  -0.0641   0.0153   1.0001
  10.250   1.5466   0.02361   0.01689  -0.0628   0.0141   1.0001
  10.500   1.5572   0.02468   0.01801  -0.0614   0.0130   1.0001
  10.750   1.5687   0.02574   0.01911  -0.0602   0.0124   1.0001
  11.000   1.5796   0.02687   0.02029  -0.0591   0.0118   1.0001
  11.250   1.5892   0.02813   0.02160  -0.0579   0.0113   1.0001
  11.500   1.5978   0.02953   0.02305  -0.0568   0.0108   1.0001
  11.750   1.6051   0.03109   0.02468  -0.0558   0.0103   1.0001
  12.000   1.6123   0.03270   0.02634  -0.0549   0.0099   1.0001
  12.250   1.6199   0.03433   0.02804  -0.0541   0.0096   1.0001
  12.500   1.6264   0.03611   0.02989  -0.0534   0.0093   1.0001
  12.750   1.6316   0.03806   0.03190  -0.0528   0.0090   1.0001
  13.000   1.6355   0.04017   0.03408  -0.0522   0.0087   1.0001
  13.250   1.6382   0.04249   0.03647  -0.0517   0.0085   1.0001
  13.500   1.6394   0.04503   0.03909  -0.0513   0.0082   1.0001
  13.750   1.6390   0.04783   0.04197  -0.0510   0.0080   1.0001
  14.000   1.6370   0.05089   0.04511  -0.0509   0.0078   1.0001
  14.250   1.6369   0.05383   0.04814  -0.0509   0.0077   1.0001
  14.500   1.6356   0.05700   0.05140  -0.0511   0.0075   1.0001
  14.750   1.6326   0.06044   0.05493  -0.0514   0.0074   1.0001
  15.000   1.6286   0.06409   0.05868  -0.0518   0.0073   1.0001
  15.250   1.6236   0.06796   0.06265  -0.0524   0.0072   1.0001
  15.500   1.6174   0.07208   0.06687  -0.0531   0.0071   1.0001
  15.750   1.6095   0.07649   0.07137  -0.0540   0.0070   1.0001
  16.000   1.6006   0.08111   0.07610  -0.0550   0.0069   1.0001
  16.250   1.5909   0.08593   0.08103  -0.0561   0.0068   1.0001
  16.500   1.5799   0.09101   0.08622  -0.0575   0.0067   1.0001
  16.750   1.5678   0.09630   0.09161  -0.0589   0.0066   1.0001
  17.000   1.5554   0.10171   0.09712  -0.0605   0.0066   1.0001
  17.250   1.5429   0.10722   0.10274  -0.0623   0.0065   1.0001
  17.500   1.5300   0.11284   0.10846  -0.0641   0.0064   1.0001
  17.750   1.5166   0.11857   0.11429  -0.0662   0.0063   1.0001
  18.000   1.5033   0.12439   0.12020  -0.0684   0.0063   1.0001
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