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RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 102 AIRFOIL (rae102-il)
Reynolds number: 200,000
Max Cl/Cd: 41.45 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae102-il-200000-n5.txt
Download as CSV file: xf-rae102-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 102 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7606   0.08610   0.08241  -0.0120   1.0000   0.0130
 -12.000  -0.7867   0.07523   0.07143  -0.0200   1.0000   0.0129
 -11.750  -0.8049   0.06810   0.06420  -0.0252   1.0000   0.0127
 -11.500  -0.8264   0.06155   0.05748  -0.0295   1.0000   0.0126
 -11.250  -0.8469   0.05619   0.05193  -0.0320   1.0000   0.0126
 -11.000  -0.8670   0.05170   0.04723  -0.0327   1.0000   0.0126
 -10.750  -0.8845   0.04809   0.04338  -0.0315   1.0000   0.0126
 -10.500  -0.9014   0.04483   0.03983  -0.0286   1.0000   0.0127
 -10.250  -0.9112   0.04174   0.03641  -0.0257   1.0000   0.0128
 -10.000  -0.9135   0.03873   0.03303  -0.0232   1.0000   0.0129
  -9.750  -0.9119   0.03570   0.02966  -0.0210   1.0000   0.0132
  -9.500  -0.9034   0.03353   0.02730  -0.0193   1.0000   0.0136
  -9.250  -0.8914   0.03162   0.02518  -0.0178   1.0000   0.0139
  -9.000  -0.8762   0.03038   0.02376  -0.0165   1.0000   0.0146
  -8.750  -0.8601   0.02906   0.02225  -0.0152   1.0000   0.0154
  -8.500  -0.8431   0.02758   0.02052  -0.0139   1.0000   0.0164
  -8.250  -0.8252   0.02594   0.01862  -0.0125   1.0000   0.0172
  -8.000  -0.8062   0.02445   0.01690  -0.0112   1.0000   0.0178
  -7.750  -0.7880   0.02282   0.01512  -0.0099   1.0000   0.0185
  -7.500  -0.7697   0.02159   0.01384  -0.0086   1.0000   0.0196
  -7.250  -0.7501   0.02071   0.01287  -0.0074   1.0000   0.0208
  -7.000  -0.7299   0.01994   0.01202  -0.0062   1.0000   0.0226
  -6.750  -0.7097   0.01916   0.01113  -0.0050   1.0000   0.0244
  -6.500  -0.6920   0.01810   0.01001  -0.0033   1.0000   0.0259
  -6.250  -0.6736   0.01728   0.00916  -0.0018   1.0000   0.0279
  -6.000  -0.6537   0.01667   0.00848  -0.0005   1.0000   0.0309
  -5.750  -0.6335   0.01612   0.00785   0.0008   1.0000   0.0341
  -5.500  -0.6150   0.01538   0.00712   0.0024   1.0000   0.0385
  -5.250  -0.5947   0.01489   0.00656   0.0037   1.0000   0.0437
  -5.000  -0.5753   0.01432   0.00602   0.0051   1.0000   0.0522
  -4.750  -0.5556   0.01382   0.00552   0.0065   1.0000   0.0632
  -4.500  -0.5361   0.01334   0.00510   0.0079   1.0000   0.0814
  -4.250  -0.5138   0.01276   0.00470   0.0085   0.9984   0.1149
  -4.000  -0.4814   0.01196   0.00424   0.0068   0.9903   0.1868
  -3.750  -0.4507   0.01100   0.00379   0.0053   0.9818   0.3039
  -3.500  -0.4219   0.01018   0.00358   0.0045   0.9720   0.4431
  -3.250  -0.3903   0.00986   0.00346   0.0036   0.9620   0.5107
  -3.000  -0.3570   0.00966   0.00335   0.0024   0.9521   0.5535
  -2.750  -0.3232   0.00950   0.00323   0.0013   0.9418   0.5878
  -2.500  -0.2909   0.00936   0.00314   0.0004   0.9295   0.6164
  -2.250  -0.2586   0.00924   0.00306  -0.0003   0.9165   0.6420
  -2.000  -0.2267   0.00914   0.00296  -0.0010   0.9026   0.6649
  -1.750  -0.1956   0.00905   0.00288  -0.0014   0.8876   0.6839
  -1.500  -0.1655   0.00897   0.00280  -0.0017   0.8721   0.7003
  -1.250  -0.1365   0.00891   0.00272  -0.0017   0.8566   0.7149
  -1.000  -0.1083   0.00887   0.00265  -0.0015   0.8407   0.7284
  -0.750  -0.0808   0.00884   0.00259  -0.0012   0.8250   0.7417
  -0.500  -0.0537   0.00882   0.00255  -0.0008   0.8099   0.7547
  -0.250  -0.0268   0.00880   0.00253  -0.0004   0.7957   0.7679
   0.000   0.0000   0.00880   0.00252   0.0000   0.7816   0.7816
   0.250   0.0268   0.00880   0.00253   0.0004   0.7679   0.7957
   0.500   0.0537   0.00882   0.00255   0.0008   0.7547   0.8099
   0.750   0.0808   0.00884   0.00259   0.0012   0.7417   0.8250
   1.000   0.1083   0.00887   0.00265   0.0015   0.7285   0.8407
   1.250   0.1365   0.00891   0.00272   0.0017   0.7150   0.8566
   1.500   0.1655   0.00897   0.00280   0.0017   0.7004   0.8722
   1.750   0.1956   0.00905   0.00288   0.0014   0.6838   0.8877
   2.000   0.2266   0.00914   0.00296   0.0010   0.6649   0.9027
   2.250   0.2586   0.00924   0.00306   0.0003   0.6420   0.9166
   2.500   0.2909   0.00936   0.00314  -0.0004   0.6164   0.9295
   2.750   0.3232   0.00950   0.00323  -0.0013   0.5878   0.9419
   3.000   0.3570   0.00966   0.00335  -0.0024   0.5537   0.9523
   3.250   0.3902   0.00986   0.00346  -0.0036   0.5102   0.9622
   3.500   0.4220   0.01018   0.00357  -0.0045   0.4421   0.9722
   3.750   0.4508   0.01098   0.00379  -0.0053   0.3062   0.9821
   4.000   0.4816   0.01196   0.00424  -0.0068   0.1877   0.9905
   4.250   0.5138   0.01276   0.00469  -0.0085   0.1147   0.9986
   4.500   0.5356   0.01333   0.00510  -0.0078   0.0817   1.0000
   4.750   0.5551   0.01381   0.00552  -0.0064   0.0633   1.0000
   5.000   0.5749   0.01431   0.00602  -0.0050   0.0523   1.0000
   5.250   0.5944   0.01488   0.00654  -0.0036   0.0437   1.0000
   5.500   0.6147   0.01537   0.00711  -0.0023   0.0386   1.0000
   5.750   0.6331   0.01612   0.00785  -0.0008   0.0340   1.0000
   6.000   0.6534   0.01667   0.00848   0.0005   0.0309   1.0000
   6.250   0.6734   0.01727   0.00915   0.0019   0.0279   1.0000
   6.500   0.6919   0.01810   0.01000   0.0033   0.0258   1.0000
   6.750   0.7097   0.01915   0.01111   0.0050   0.0243   1.0000
   7.000   0.7299   0.01995   0.01203   0.0062   0.0226   1.0000
   7.250   0.7502   0.02069   0.01285   0.0074   0.0207   1.0000
   7.500   0.7699   0.02157   0.01381   0.0085   0.0195   1.0000
   7.750   0.7882   0.02283   0.01513   0.0098   0.0185   1.0000
   8.000   0.8065   0.02444   0.01688   0.0112   0.0178   1.0000
   8.250   0.8255   0.02595   0.01863   0.0125   0.0172   1.0000
   8.500   0.8435   0.02760   0.02054   0.0138   0.0165   1.0000
   8.750   0.8607   0.02903   0.02221   0.0151   0.0154   1.0000
   9.000   0.8768   0.03042   0.02381   0.0164   0.0146   1.0000
   9.250   0.8920   0.03170   0.02527   0.0176   0.0139   1.0000
   9.500   0.9046   0.03336   0.02709   0.0191   0.0135   1.0000
   9.750   0.9130   0.03572   0.02970   0.0208   0.0132   1.0000
  10.000   0.9148   0.03875   0.03303   0.0230   0.0130   1.0000
  10.250   0.9127   0.04171   0.03637   0.0254   0.0128   1.0000
  10.500   0.9032   0.04483   0.03982   0.0283   0.0127   1.0000
  10.750   0.8871   0.04800   0.04327   0.0312   0.0127   1.0000
  11.000   0.8670   0.05189   0.04743   0.0324   0.0126   1.0000
  11.250   0.8490   0.05613   0.05187   0.0318   0.0126   1.0000
  11.500   0.8302   0.06122   0.05713   0.0295   0.0127   1.0000
  11.750   0.8066   0.06814   0.06423   0.0249   0.0127   1.0000
  12.000   0.7850   0.07608   0.07230   0.0190   0.0128   1.0000
  12.250   0.7477   0.09153   0.08792   0.0081   0.0132   1.0000
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