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USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 41 AIRFOIL (usa41-il)
Reynolds number: 500,000
Max Cl/Cd: 107.8 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa41-il-500000.txt
Download as CSV file: xf-usa41-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 41 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3467   0.08894   0.08678  -0.0261   1.0000   0.0195
  -7.500  -0.3531   0.08683   0.08473  -0.0251   1.0000   0.0195
  -7.250  -0.3553   0.08427   0.08222  -0.0254   1.0000   0.0196
  -7.000  -0.3610   0.08212   0.08011  -0.0246   1.0000   0.0196
  -6.750  -0.3424   0.07742   0.07540  -0.0308   0.9978   0.0197
  -6.500  -0.3209   0.07015   0.06812  -0.0389   0.9944   0.0202
  -6.250  -0.2988   0.06725   0.06520  -0.0416   0.9909   0.0208
  -6.000  -0.2697   0.06353   0.06145  -0.0474   0.9872   0.0217
  -5.750  -0.2339   0.05866   0.05653  -0.0562   0.9841   0.0228
  -5.500  -0.1822   0.05178   0.04951  -0.0701   0.9779   0.0262
  -5.250  -0.1392   0.04497   0.04251  -0.0797   0.9738   0.0264
  -4.750  -0.0764   0.03428   0.03153  -0.0911   0.9649   0.0291
  -4.500  -0.0397   0.03063   0.02767  -0.0953   0.9607   0.0321
  -4.250   0.0004   0.02218   0.01840  -0.1011   0.9564   0.0375
  -4.000   0.0279   0.02114   0.01739  -0.1017   0.9485   0.0395
  -3.750   0.0655   0.02199   0.01796  -0.1028   0.9432   0.0470
  -3.500   0.0892   0.01801   0.01382  -0.1040   0.9335   0.0522
  -3.250   0.1188   0.01686   0.01240  -0.1047   0.9250   0.0628
  -3.000   0.1489   0.01297   0.00777  -0.1038   0.9156   0.0426
  -2.750   0.1761   0.01152   0.00598  -0.1031   0.9050   0.0397
  -2.500   0.2034   0.01075   0.00504  -0.1026   0.8945   0.0391
  -2.250   0.2304   0.01016   0.00432  -0.1021   0.8839   0.0393
  -2.000   0.2565   0.00970   0.00378  -0.1014   0.8718   0.0404
  -1.750   0.2824   0.00926   0.00326  -0.1007   0.8592   0.0407
  -1.500   0.3084   0.00890   0.00284  -0.1000   0.8458   0.0412
  -1.250   0.3344   0.00862   0.00249  -0.0993   0.8313   0.0420
  -1.000   0.3604   0.00840   0.00219  -0.0987   0.8151   0.0427
  -0.750   0.3864   0.00824   0.00194  -0.0980   0.7975   0.0435
  -0.500   0.4122   0.00813   0.00175  -0.0973   0.7770   0.0446
  -0.250   0.4379   0.00808   0.00158  -0.0966   0.7554   0.0461
   0.000   0.4637   0.00806   0.00144  -0.0959   0.7323   0.0473
   0.250   0.4892   0.00807   0.00134  -0.0951   0.7090   0.0531
   0.500   0.5140   0.00789   0.00137  -0.0944   0.6847   0.1480
   0.750   0.5395   0.00799   0.00143  -0.0938   0.6606   0.1841
   1.000   0.5649   0.00810   0.00147  -0.0932   0.6370   0.2009
   1.250   0.5904   0.00820   0.00151  -0.0926   0.6138   0.2162
   1.500   0.6157   0.00828   0.00155  -0.0920   0.5931   0.2340
   1.750   0.6411   0.00830   0.00160  -0.0915   0.5740   0.2622
   2.000   0.6593   0.00738   0.00182  -0.0898   0.5579   0.7193
   2.250   0.7083   0.00710   0.00189  -0.0945   0.5393   1.0000
   2.500   0.7339   0.00728   0.00199  -0.0939   0.5241   1.0000
   2.750   0.7596   0.00746   0.00208  -0.0934   0.5095   1.0000
   3.000   0.7853   0.00763   0.00219  -0.0929   0.4953   1.0000
   3.250   0.8110   0.00780   0.00231  -0.0924   0.4813   1.0000
   3.500   0.8366   0.00798   0.00245  -0.0919   0.4673   1.0000
   3.750   0.8623   0.00815   0.00258  -0.0914   0.4539   1.0000
   4.000   0.8880   0.00833   0.00273  -0.0909   0.4414   1.0000
   4.250   0.9136   0.00851   0.00289  -0.0904   0.4296   1.0000
   4.500   0.9389   0.00871   0.00307  -0.0898   0.4143   1.0000
   4.750   0.9632   0.00897   0.00322  -0.0891   0.3893   1.0000
   5.000   0.9877   0.00922   0.00341  -0.0885   0.3655   1.0000
   5.250   1.0122   0.00950   0.00362  -0.0879   0.3446   1.0000
   5.500   1.0366   0.00978   0.00387  -0.0872   0.3237   1.0000
   5.750   1.0600   0.01016   0.00413  -0.0864   0.2933   1.0000
   6.000   1.0815   0.01075   0.00448  -0.0854   0.2414   1.0000
   6.250   1.0949   0.01228   0.00531  -0.0834   0.1208   1.0000
   6.500   1.1064   0.01414   0.00658  -0.0809   0.0307   1.0000
   6.750   1.1283   0.01474   0.00727  -0.0798   0.0257   1.0000
   7.000   1.1482   0.01555   0.00813  -0.0784   0.0218   1.0000
   7.250   1.1675   0.01639   0.00908  -0.0769   0.0200   1.0000
   7.500   1.1876   0.01708   0.00986  -0.0756   0.0188   1.0000
   7.750   1.2064   0.01788   0.01073  -0.0741   0.0176   1.0000
   8.000   1.2240   0.01875   0.01168  -0.0725   0.0166   1.0000
   8.250   1.2375   0.01998   0.01297  -0.0703   0.0154   1.0000
   8.500   1.2451   0.02184   0.01495  -0.0672   0.0145   1.0000
   8.750   1.2624   0.02266   0.01586  -0.0656   0.0141   1.0000
   9.000   1.2774   0.02374   0.01703  -0.0636   0.0136   1.0000
   9.250   1.2910   0.02503   0.01843  -0.0615   0.0132   1.0000
   9.500   1.3048   0.02633   0.01984  -0.0595   0.0127   1.0000
   9.750   1.3179   0.02779   0.02140  -0.0575   0.0124   1.0000
  10.000   1.3306   0.02933   0.02304  -0.0554   0.0120   1.0000
  10.250   1.3424   0.03090   0.02471  -0.0533   0.0117   1.0000
  10.500   1.3519   0.03223   0.02613  -0.0510   0.0112   1.0000
  10.750   1.3618   0.03413   0.02812  -0.0490   0.0109   1.0000
  11.000   1.3747   0.03916   0.03339  -0.0484   0.0103   1.0000
  11.250   1.3784   0.04253   0.03702  -0.0459   0.0103   1.0000
  11.500   1.3787   0.04481   0.03950  -0.0430   0.0103   1.0000
  11.750   1.3749   0.04757   0.04247  -0.0401   0.0103   1.0000
  12.000   1.3659   0.05092   0.04606  -0.0373   0.0103   1.0000
  12.250   1.3560   0.05407   0.04943  -0.0349   0.0103   1.0000
  12.500   1.3503   0.05637   0.05187  -0.0332   0.0104   1.0000
  12.750   1.3391   0.05979   0.05549  -0.0320   0.0104   1.0000
  13.000   1.3227   0.06425   0.06016  -0.0315   0.0104   1.0000
  13.250   1.3191   0.06649   0.06254  -0.0314   0.0106   1.0000
  13.500   1.3022   0.07135   0.06762  -0.0323   0.0107   1.0000
  14.000   1.0819   0.09687   0.09421  -0.0418   0.0125   1.0000
  14.250   1.0524   0.10450   0.10201  -0.0466   0.0125   1.0000
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