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N-10 (n10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.37 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n10-il-1000000-n5.txt
Download as CSV file: xf-n10-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-10                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -1.1057   0.03592   0.03314  -0.0942   0.9999   0.0078
 -16.500  -1.1200   0.03297   0.03001  -0.0924   0.9999   0.0078
 -16.250  -1.1222   0.03077   0.02766  -0.0906   0.9999   0.0080
 -16.000  -1.1189   0.02899   0.02574  -0.0886   0.9999   0.0081
 -15.750  -1.1120   0.02748   0.02410  -0.0866   0.9999   0.0083
 -15.500  -1.1024   0.02617   0.02265  -0.0847   0.9999   0.0085
 -15.250  -1.0925   0.02480   0.02116  -0.0827   0.9999   0.0088
 -15.000  -1.0737   0.02340   0.01962  -0.0824   0.9992   0.0092
 -14.750  -1.0484   0.02216   0.01828  -0.0830   0.9979   0.0097
 -14.500  -1.0219   0.02109   0.01709  -0.0837   0.9965   0.0102
 -14.250  -0.9939   0.02012   0.01602  -0.0844   0.9952   0.0106
 -14.000  -0.9650   0.01926   0.01505  -0.0852   0.9942   0.0111
 -13.750  -0.9388   0.01846   0.01417  -0.0854   0.9922   0.0118
 -13.500  -0.9109   0.01777   0.01342  -0.0857   0.9902   0.0125
 -13.250  -0.8817   0.01715   0.01275  -0.0863   0.9884   0.0133
 -13.000  -0.8514   0.01656   0.01207  -0.0870   0.9868   0.0141
 -12.750  -0.8203   0.01605   0.01151  -0.0879   0.9855   0.0149
 -12.500  -0.7900   0.01571   0.01117  -0.0884   0.9838   0.0158
 -12.250  -0.7623   0.01538   0.01081  -0.0884   0.9801   0.0167
 -12.000  -0.7325   0.01500   0.01037  -0.0888   0.9768   0.0175
 -11.750  -0.7016   0.01459   0.00989  -0.0894   0.9741   0.0180
 -11.500  -0.6752   0.01418   0.00942  -0.0891   0.9682   0.0185
 -11.250  -0.6447   0.01385   0.00907  -0.0896   0.9629   0.0192
 -11.000  -0.6160   0.01363   0.00884  -0.0897   0.9549   0.0198
 -10.750  -0.5862   0.01341   0.00859  -0.0899   0.9474   0.0205
 -10.500  -0.5580   0.01315   0.00827  -0.0899   0.9371   0.0211
 -10.250  -0.5301   0.01286   0.00791  -0.0898   0.9248   0.0217
 -10.000  -0.5026   0.01263   0.00759  -0.0895   0.9102   0.0222
  -9.750  -0.4755   0.01244   0.00729  -0.0891   0.8949   0.0226
  -9.500  -0.4487   0.01226   0.00701  -0.0887   0.8788   0.0229
  -9.250  -0.4231   0.01187   0.00649  -0.0882   0.8619   0.0235
  -9.000  -0.3972   0.01151   0.00603  -0.0877   0.8468   0.0242
  -8.750  -0.3704   0.01128   0.00574  -0.0874   0.8350   0.0248
  -8.500  -0.3432   0.01110   0.00548  -0.0871   0.8250   0.0253
  -8.250  -0.3160   0.01088   0.00519  -0.0868   0.8150   0.0258
  -8.000  -0.2885   0.01067   0.00493  -0.0866   0.8070   0.0264
  -7.750  -0.2611   0.01045   0.00463  -0.0864   0.7990   0.0269
  -7.500  -0.2335   0.01021   0.00433  -0.0862   0.7909   0.0273
  -7.250  -0.2060   0.01001   0.00406  -0.0860   0.7817   0.0277
  -7.000  -0.1783   0.00982   0.00381  -0.0858   0.7712   0.0281
  -6.750  -0.1506   0.00966   0.00359  -0.0857   0.7603   0.0285
  -6.500  -0.1229   0.00953   0.00338  -0.0855   0.7481   0.0287
  -6.250  -0.0952   0.00939   0.00317  -0.0853   0.7344   0.0289
  -6.000  -0.0678   0.00916   0.00286  -0.0851   0.7180   0.0295
  -5.750  -0.0405   0.00901   0.00260  -0.0848   0.6971   0.0302
  -5.500  -0.0134   0.00892   0.00240  -0.0846   0.6746   0.0310
  -5.250   0.0140   0.00885   0.00225  -0.0844   0.6554   0.0317
  -5.000   0.0416   0.00879   0.00211  -0.0842   0.6403   0.0326
  -4.500   0.0975   0.00867   0.00188  -0.0840   0.6170   0.0345
  -4.250   0.1256   0.00862   0.00179  -0.0840   0.6065   0.0355
  -4.000   0.1537   0.00858   0.00170  -0.0839   0.5969   0.0371
  -3.750   0.1820   0.00849   0.00161  -0.0840   0.5889   0.0411
  -3.500   0.2100   0.00844   0.00154  -0.0839   0.5798   0.0458
  -3.250   0.2382   0.00835   0.00148  -0.0840   0.5692   0.0591
  -3.000   0.2661   0.00828   0.00144  -0.0839   0.5563   0.0777
  -2.750   0.2939   0.00825   0.00140  -0.0839   0.5395   0.0918
  -2.500   0.3214   0.00828   0.00137  -0.0838   0.5154   0.1040
  -2.250   0.3478   0.00838   0.00136  -0.0836   0.4739   0.1231
  -2.000   0.3733   0.00847   0.00143  -0.0833   0.4292   0.1839
  -1.750   0.3995   0.00864   0.00151  -0.0831   0.3951   0.2059
  -1.500   0.4266   0.00873   0.00156  -0.0830   0.3731   0.2275
  -1.250   0.4541   0.00877   0.00160  -0.0830   0.3606   0.2458
  -0.750   0.5088   0.00857   0.00170  -0.0831   0.3430   0.3797
  -0.500   0.5359   0.00848   0.00178  -0.0831   0.3344   0.4569
  -0.250   0.5632   0.00839   0.00185  -0.0832   0.3271   0.5300
   0.000   0.5899   0.00821   0.00193  -0.0831   0.3205   0.6342
   0.250   0.6156   0.00796   0.00203  -0.0828   0.3161   0.7626
   0.500   0.6393   0.00775   0.00213  -0.0818   0.3123   0.8680
   0.750   0.6664   0.00768   0.00223  -0.0814   0.3075   0.9737
   1.000   0.7039   0.00780   0.00231  -0.0836   0.3018   1.0001
   1.250   0.7311   0.00789   0.00238  -0.0836   0.2992   1.0001
   1.500   0.7583   0.00799   0.00246  -0.0835   0.2959   1.0001
   1.750   0.7853   0.00811   0.00255  -0.0835   0.2913   1.0001
   2.000   0.8121   0.00824   0.00266  -0.0834   0.2871   1.0001
   2.250   0.8394   0.00834   0.00276  -0.0834   0.2843   1.0001
   2.500   0.8667   0.00845   0.00286  -0.0834   0.2810   1.0001
   2.750   0.8937   0.00857   0.00297  -0.0834   0.2767   1.0001
   3.000   0.9203   0.00873   0.00310  -0.0833   0.2713   1.0001
   3.250   0.9475   0.00884   0.00322  -0.0833   0.2672   1.0001
   3.500   0.9743   0.00899   0.00335  -0.0833   0.2612   1.0001
   3.750   1.0007   0.00915   0.00349  -0.0832   0.2541   1.0001
   4.000   1.0264   0.00939   0.00366  -0.0831   0.2378   1.0001
   4.250   1.0480   0.00997   0.00397  -0.0823   0.1891   1.0001
   4.500   1.0682   0.01068   0.00444  -0.0813   0.1487   1.0001
   4.750   1.0919   0.01108   0.00476  -0.0808   0.1339   1.0001
   5.000   1.1166   0.01138   0.00503  -0.0805   0.1254   1.0001
   5.250   1.1407   0.01172   0.00532  -0.0801   0.1166   1.0001
   5.500   1.1656   0.01198   0.00558  -0.0799   0.1110   1.0001
   5.750   1.1899   0.01228   0.00586  -0.0795   0.1057   1.0001
   6.000   1.2142   0.01257   0.00614  -0.0792   0.0999   1.0001
   6.250   1.2372   0.01296   0.00647  -0.0787   0.0894   1.0001
   6.500   1.2573   0.01359   0.00693  -0.0778   0.0647   1.0001
   6.750   1.2735   0.01450   0.00768  -0.0762   0.0370   1.0001
   7.000   1.2890   0.01544   0.00849  -0.0745   0.0155   1.0001
   7.250   1.3103   0.01588   0.00894  -0.0737   0.0134   1.0001
   7.500   1.3306   0.01636   0.00944  -0.0728   0.0118   1.0001
   7.750   1.3511   0.01680   0.00991  -0.0720   0.0108   1.0001
   8.000   1.3711   0.01724   0.01039  -0.0710   0.0102   1.0001
   8.250   1.3898   0.01772   0.01089  -0.0699   0.0096   1.0001
   8.500   1.4060   0.01824   0.01144  -0.0683   0.0090   1.0001
   8.750   1.4207   0.01884   0.01208  -0.0664   0.0084   1.0001
   9.000   1.4362   0.01940   0.01269  -0.0648   0.0081   1.0001
   9.250   1.4516   0.01998   0.01332  -0.0633   0.0078   1.0001
   9.500   1.4665   0.02060   0.01398  -0.0618   0.0074   1.0001
   9.750   1.4807   0.02128   0.01470  -0.0602   0.0071   1.0001
  10.000   1.4939   0.02203   0.01550  -0.0586   0.0068   1.0001
  10.250   1.5059   0.02288   0.01640  -0.0570   0.0065   1.0001
  10.500   1.5162   0.02388   0.01745  -0.0553   0.0062   1.0001
  10.750   1.5259   0.02496   0.01860  -0.0536   0.0060   1.0001
  11.000   1.5367   0.02600   0.01971  -0.0522   0.0059   1.0001
  11.250   1.5466   0.02715   0.02093  -0.0509   0.0057   1.0001
  11.500   1.5556   0.02843   0.02227  -0.0496   0.0056   1.0001
  11.750   1.5638   0.02981   0.02373  -0.0484   0.0054   1.0001
  12.000   1.5710   0.03134   0.02533  -0.0473   0.0053   1.0001
  12.250   1.5773   0.03301   0.02707  -0.0463   0.0052   1.0001
  12.500   1.5826   0.03482   0.02897  -0.0454   0.0050   1.0001
  12.750   1.5869   0.03680   0.03102  -0.0446   0.0049   1.0001
  13.000   1.5898   0.03897   0.03328  -0.0439   0.0048   1.0001
  13.250   1.5915   0.04135   0.03574  -0.0434   0.0047   1.0001
  13.500   1.5916   0.04402   0.03849  -0.0430   0.0046   1.0001
  13.750   1.5892   0.04705   0.04161  -0.0428   0.0045   1.0001
  14.000   1.5845   0.05052   0.04519  -0.0428   0.0044   1.0001
  14.250   1.5765   0.05455   0.04933  -0.0431   0.0043   1.0001
  14.500   1.5716   0.05828   0.05317  -0.0435   0.0042   1.0001
  14.750   1.5657   0.06225   0.05724  -0.0441   0.0042   1.0001
  15.000   1.5587   0.06650   0.06160  -0.0450   0.0042   1.0001
  15.250   1.5486   0.07132   0.06654  -0.0461   0.0041   1.0001
  15.500   1.5378   0.07637   0.07171  -0.0474   0.0041   1.0001
  15.750   1.5258   0.08175   0.07721  -0.0489   0.0041   1.0001
  16.000   1.5119   0.08756   0.08315  -0.0507   0.0040   1.0001
  16.250   1.4975   0.09351   0.08922  -0.0526   0.0040   1.0001
  16.500   1.4829   0.09952   0.09535  -0.0546   0.0040   1.0001
  16.750   1.4670   0.10583   0.10177  -0.0568   0.0040   1.0001
  17.000   1.4518   0.11205   0.10810  -0.0591   0.0040   1.0001
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