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N-10 (n10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: N-10 (n10-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.73 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n10-il-1000000.txt
Download as CSV file: xf-n10-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.9998   0.03592   0.03338  -0.0888   0.9999   0.0139
 -15.250  -1.0080   0.03333   0.03061  -0.0871   0.9999   0.0140
 -15.000  -1.0050   0.03165   0.02880  -0.0853   0.9999   0.0141
 -14.750  -1.0146   0.02869   0.02560  -0.0825   0.9999   0.0145
 -14.500  -1.0047   0.02756   0.02441  -0.0806   0.9999   0.0148
 -14.250  -0.9875   0.02715   0.02400  -0.0790   0.9999   0.0151
 -14.000  -0.9689   0.02691   0.02376  -0.0775   0.9999   0.0154
 -13.750  -0.9512   0.02656   0.02340  -0.0759   0.9999   0.0157
 -13.500  -0.9350   0.02600   0.02277  -0.0742   0.9999   0.0161
 -13.250  -0.9201   0.02522   0.02190  -0.0724   0.9999   0.0164
 -13.000  -0.8946   0.02424   0.02078  -0.0728   0.9991   0.0169
 -12.750  -0.8636   0.02341   0.01982  -0.0741   0.9978   0.0173
 -12.500  -0.8357   0.02163   0.01780  -0.0756   0.9962   0.0179
 -12.250  -0.8038   0.02083   0.01695  -0.0770   0.9949   0.0184
 -12.000  -0.7691   0.02065   0.01678  -0.0785   0.9940   0.0189
 -11.750  -0.7371   0.02046   0.01658  -0.0794   0.9920   0.0194
 -11.500  -0.7048   0.02011   0.01616  -0.0804   0.9899   0.0200
 -11.250  -0.6722   0.01956   0.01553  -0.0816   0.9879   0.0206
 -11.000  -0.6390   0.01901   0.01485  -0.0829   0.9863   0.0212
 -10.750  -0.6046   0.01874   0.01450  -0.0843   0.9851   0.0215
 -10.500  -0.5751   0.01672   0.01230  -0.0858   0.9838   0.0226
 -10.250  -0.5440   0.01644   0.01202  -0.0865   0.9808   0.0232
 -10.000  -0.5121   0.01615   0.01169  -0.0874   0.9776   0.0238
  -9.750  -0.4800   0.01567   0.01115  -0.0883   0.9746   0.0245
  -9.500  -0.4476   0.01511   0.01051  -0.0893   0.9718   0.0252
  -9.250  -0.4199   0.01470   0.01001  -0.0891   0.9647   0.0258
  -9.000  -0.3887   0.01455   0.00979  -0.0896   0.9583   0.0263
  -8.750  -0.3647   0.01298   0.00807  -0.0892   0.9473   0.0273
  -8.500  -0.3373   0.01243   0.00748  -0.0890   0.9361   0.0279
  -8.250  -0.3098   0.01205   0.00704  -0.0888   0.9230   0.0286
  -8.000  -0.2826   0.01178   0.00669  -0.0885   0.9077   0.0294
  -7.750  -0.2559   0.01146   0.00627  -0.0880   0.8921   0.0301
  -7.500  -0.2293   0.01113   0.00584  -0.0876   0.8779   0.0307
  -7.250  -0.2025   0.01083   0.00544  -0.0872   0.8659   0.0313
  -7.000  -0.1753   0.01059   0.00512  -0.0869   0.8548   0.0317
  -6.750  -0.1476   0.01046   0.00492  -0.0866   0.8444   0.0321
  -6.500  -0.1222   0.00970   0.00404  -0.0861   0.8344   0.0332
  -6.250  -0.0953   0.00936   0.00364  -0.0858   0.8242   0.0341
  -6.000  -0.0678   0.00913   0.00337  -0.0856   0.8147   0.0350
  -5.500  -0.0123   0.00876   0.00290  -0.0853   0.7965   0.0369
  -5.250   0.0156   0.00863   0.00271  -0.0851   0.7873   0.0380
  -5.000   0.0436   0.00849   0.00252  -0.0850   0.7768   0.0388
  -4.750   0.0713   0.00829   0.00226  -0.0848   0.7653   0.0401
  -4.500   0.0990   0.00811   0.00203  -0.0846   0.7520   0.0427
  -4.250   0.1268   0.00800   0.00188  -0.0845   0.7368   0.0454
  -4.000   0.1546   0.00791   0.00173  -0.0843   0.7208   0.0492
  -3.750   0.1822   0.00776   0.00161  -0.0842   0.7043   0.0643
  -3.500   0.2096   0.00762   0.00151  -0.0840   0.6875   0.0941
  -3.250   0.2371   0.00752   0.00142  -0.0839   0.6719   0.1177
  -3.000   0.2642   0.00733   0.00139  -0.0839   0.6581   0.1852
  -2.750   0.2920   0.00729   0.00138  -0.0838   0.6458   0.2113
  -2.500   0.3198   0.00729   0.00136  -0.0837   0.6343   0.2311
  -2.250   0.3478   0.00724   0.00135  -0.0838   0.6235   0.2526
  -2.000   0.3756   0.00715   0.00134  -0.0838   0.6132   0.2938
  -1.750   0.4022   0.00684   0.00136  -0.0838   0.6012   0.4225
  -1.500   0.4286   0.00656   0.00140  -0.0836   0.5866   0.5520
  -1.250   0.4532   0.00611   0.00146  -0.0831   0.5699   0.7356
  -1.000   0.4735   0.00577   0.00155  -0.0811   0.5524   0.8953
  -0.750   0.5012   0.00584   0.00160  -0.0807   0.5210   0.9698
  -0.500   0.5373   0.00623   0.00168  -0.0828   0.4548   0.9921
  -0.250   0.5735   0.00659   0.00180  -0.0848   0.4116   1.0001
   0.000   0.5979   0.00681   0.00190  -0.0842   0.3900   1.0001
   0.250   0.6230   0.00699   0.00198  -0.0837   0.3745   1.0001
   0.500   0.6488   0.00715   0.00206  -0.0833   0.3623   1.0001
   0.750   0.6749   0.00730   0.00215  -0.0830   0.3531   1.0001
   1.000   0.7013   0.00744   0.00224  -0.0828   0.3455   1.0001
   1.250   0.7278   0.00758   0.00233  -0.0826   0.3390   1.0001
   1.500   0.7547   0.00770   0.00242  -0.0825   0.3335   1.0001
   1.750   0.7814   0.00784   0.00253  -0.0824   0.3281   1.0001
   2.000   0.8083   0.00797   0.00264  -0.0823   0.3237   1.0001
   2.250   0.8355   0.00808   0.00274  -0.0823   0.3195   1.0001
   2.500   0.8624   0.00822   0.00285  -0.0822   0.3150   1.0001
   2.750   0.8889   0.00838   0.00299  -0.0821   0.3105   1.0001
   3.000   0.9162   0.00849   0.00311  -0.0821   0.3074   1.0001
   3.250   0.9433   0.00860   0.00323  -0.0821   0.3036   1.0001
   3.500   0.9701   0.00875   0.00336  -0.0821   0.2988   1.0001
   3.750   0.9964   0.00893   0.00352  -0.0820   0.2936   1.0001
   4.000   1.0237   0.00902   0.00364  -0.0820   0.2876   1.0001
   4.250   1.0499   0.00921   0.00379  -0.0819   0.2798   1.0001
   4.500   1.0768   0.00933   0.00392  -0.0820   0.2727   1.0001
   4.750   1.1028   0.00954   0.00409  -0.0819   0.2630   1.0001
   5.000   1.1284   0.00975   0.00426  -0.0817   0.2474   1.0001
   5.250   1.1518   0.01016   0.00450  -0.0812   0.2136   1.0001
   5.500   1.1696   0.01104   0.00505  -0.0799   0.1605   1.0001
   5.750   1.1913   0.01159   0.00548  -0.0791   0.1409   1.0001
   6.000   1.2146   0.01197   0.00582  -0.0786   0.1304   1.0001
   6.250   1.2382   0.01233   0.00615  -0.0782   0.1224   1.0001
   6.500   1.2620   0.01265   0.00646  -0.0778   0.1165   1.0001
   6.750   1.2852   0.01301   0.00681  -0.0773   0.1094   1.0001
   7.000   1.3082   0.01338   0.00714  -0.0768   0.1007   1.0001
   7.250   1.3293   0.01387   0.00754  -0.0761   0.0850   1.0001
   7.500   1.3358   0.01550   0.00875  -0.0730   0.0289   1.0001
   7.750   1.3514   0.01635   0.00954  -0.0713   0.0182   1.0001
   8.000   1.3690   0.01700   0.01021  -0.0700   0.0158   1.0001
   8.250   1.3879   0.01751   0.01076  -0.0688   0.0150   1.0001
   8.500   1.4046   0.01806   0.01137  -0.0673   0.0142   1.0001
   8.750   1.4181   0.01873   0.01208  -0.0652   0.0134   1.0001
   9.000   1.4283   0.01962   0.01304  -0.0627   0.0126   1.0001
   9.250   1.4432   0.02024   0.01371  -0.0611   0.0122   1.0001
   9.500   1.4570   0.02093   0.01446  -0.0594   0.0118   1.0001
   9.750   1.4694   0.02172   0.01531  -0.0576   0.0114   1.0001
  10.000   1.4808   0.02261   0.01626  -0.0558   0.0110   1.0001
  10.250   1.4909   0.02360   0.01731  -0.0539   0.0106   1.0001
  10.500   1.4985   0.02481   0.01859  -0.0519   0.0103   1.0001
  10.750   1.5008   0.02646   0.02034  -0.0496   0.0100   1.0001
  11.000   1.5000   0.02847   0.02247  -0.0473   0.0097   1.0001
  11.250   1.5089   0.02981   0.02387  -0.0462   0.0096   1.0001
  11.500   1.5159   0.03137   0.02552  -0.0450   0.0094   1.0001
  11.750   1.5210   0.03316   0.02739  -0.0439   0.0092   1.0001
  12.000   1.5247   0.03516   0.02948  -0.0429   0.0090   1.0001
  12.250   1.5278   0.03730   0.03171  -0.0421   0.0088   1.0001
  12.500   1.5293   0.03967   0.03417  -0.0415   0.0087   1.0001
  12.750   1.5299   0.04224   0.03683  -0.0410   0.0085   1.0001
  13.000   1.5298   0.04502   0.03969  -0.0407   0.0083   1.0001
  13.250   1.5277   0.04813   0.04289  -0.0407   0.0082   1.0001
  13.500   1.5236   0.05159   0.04645  -0.0408   0.0081   1.0001
  13.750   1.5182   0.05536   0.05032  -0.0412   0.0079   1.0001
  14.000   1.5096   0.05967   0.05473  -0.0418   0.0078   1.0001
  14.250   1.4982   0.06448   0.05965  -0.0426   0.0077   1.0001
  14.500   1.4851   0.06971   0.06500  -0.0437   0.0077   1.0001
  14.750   1.4706   0.07529   0.07070  -0.0451   0.0076   1.0001
  15.000   1.4548   0.08119   0.07672  -0.0467   0.0075   1.0001
  15.250   1.4370   0.08749   0.08314  -0.0485   0.0075   1.0001
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