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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 100,000
Max Cl/Cd: 50.42 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ec863914-il-100000.txt
Download as CSV file: xf-ec863914-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5070   0.10159   0.09736  -0.0397   1.0000   0.0595
  -9.000  -0.5186   0.09650   0.09232  -0.0401   1.0000   0.0563
  -8.750  -0.6500   0.07655   0.07226  -0.0534   1.0000   0.0506
  -8.500  -0.6805   0.07327   0.06879  -0.0544   1.0000   0.0500
  -8.250  -0.6779   0.06942   0.06494  -0.0533   1.0000   0.0484
  -8.000  -0.6893   0.06434   0.05971  -0.0551   1.0000   0.0476
  -7.750  -0.6928   0.05926   0.05442  -0.0566   1.0000   0.0454
  -7.500  -0.6903   0.05369   0.04840  -0.0598   1.0000   0.0449
  -7.250  -0.6763   0.04784   0.04184  -0.0634   1.0000   0.0423
  -7.000  -0.6514   0.04304   0.03617  -0.0668   1.0000   0.0403
  -6.750  -0.6246   0.04066   0.03323  -0.0680   1.0000   0.0388
  -6.500  -0.5991   0.03920   0.03145  -0.0684   1.0000   0.0380
  -6.250  -0.5746   0.03701   0.02899  -0.0686   1.0000   0.0376
  -6.000  -0.5506   0.03495   0.02677  -0.0685   1.0000   0.0374
  -5.750  -0.5268   0.03338   0.02509  -0.0681   1.0000   0.0374
  -5.500  -0.5029   0.03215   0.02380  -0.0678   1.0000   0.0375
  -5.250  -0.4776   0.03108   0.02271  -0.0678   1.0000   0.0379
  -5.000  -0.4472   0.02969   0.02124  -0.0694   1.0000   0.0390
  -4.750  -0.4128   0.02864   0.02006  -0.0720   1.0000   0.0411
  -4.500  -0.3792   0.02793   0.01918  -0.0742   1.0000   0.0447
  -4.250  -0.3451   0.02729   0.01843  -0.0762   1.0000   0.0526
  -4.000  -0.3002   0.02616   0.01833  -0.0815   1.0000   0.2295
  -3.750  -0.2683   0.02640   0.01859  -0.0837   1.0000   0.2818
  -3.500  -0.2399   0.02661   0.01878  -0.0849   1.0000   0.3109
  -3.250  -0.2128   0.02682   0.01898  -0.0856   1.0000   0.3338
  -3.000  -0.1870   0.02701   0.01920  -0.0861   1.0000   0.3510
  -2.750  -0.1601   0.02726   0.01951  -0.0869   1.0000   0.3779
  -2.500  -0.1343   0.02750   0.01984  -0.0873   1.0000   0.4009
  -2.250  -0.1076   0.02773   0.02026  -0.0881   1.0000   0.4364
  -2.000  -0.0823   0.02799   0.02099  -0.0883   1.0000   0.4982
  -1.750  -0.0714   0.02862   0.02215  -0.0849   1.0000   0.5606
  -1.500  -0.0629   0.02959   0.02327  -0.0810   1.0000   0.6237
  -1.250  -0.0522   0.03070   0.02434  -0.0778   1.0000   0.6674
  -1.000  -0.0294   0.03251   0.02607  -0.0761   0.9941   0.6979
  -0.750   0.0331   0.03489   0.02826  -0.0797   0.9582   0.7286
  -0.500   0.0631   0.03587   0.02917  -0.0788   0.9436   0.7494
  -0.250   0.0893   0.03637   0.02957  -0.0777   0.9305   0.7683
   0.000   0.1096   0.03662   0.02977  -0.0755   0.9181   0.7837
   0.250   0.1304   0.03676   0.02987  -0.0735   0.9059   0.7988
   0.500   0.1516   0.03682   0.02988  -0.0716   0.8942   0.8136
   0.750   0.1752   0.03681   0.02983  -0.0703   0.8831   0.8279
   1.000   0.2030   0.03673   0.02971  -0.0697   0.8733   0.8418
   1.250   0.2335   0.03652   0.02944  -0.0696   0.8639   0.8553
   1.500   0.2591   0.03627   0.02916  -0.0690   0.8522   0.8671
   1.750   0.2830   0.03588   0.02876  -0.0680   0.8410   0.8781
   2.000   0.3092   0.03538   0.02825  -0.0671   0.8312   0.8896
   2.250   0.3398   0.03463   0.02749  -0.0666   0.8231   0.9040
   2.500   0.3577   0.03391   0.02677  -0.0642   0.8111   0.9197
   2.750   0.3756   0.03296   0.02583  -0.0615   0.7994   0.9351
   3.000   0.3992   0.03197   0.02486  -0.0599   0.7886   0.9494
   3.250   0.4381   0.03062   0.02353  -0.0605   0.7816   0.9631
   3.500   0.4730   0.02975   0.02269  -0.0613   0.7694   0.9733
   3.750   0.5138   0.02895   0.02196  -0.0633   0.7580   0.9792
   4.000   0.5700   0.02748   0.02054  -0.0670   0.7530   0.9835
   4.250   0.6092   0.02652   0.01965  -0.0685   0.7407   0.9900
   4.750   0.6955   0.02406   0.01735  -0.0721   0.7195   1.0000
   5.000   0.7495   0.02241   0.01579  -0.0752   0.7102   1.0000
   5.250   0.7917   0.02143   0.01488  -0.0769   0.6913   1.0000
   5.500   0.8425   0.02023   0.01372  -0.0798   0.6682   1.0000
   5.750   0.8919   0.01939   0.01283  -0.0826   0.6343   1.0000
   6.000   0.9366   0.01906   0.01233  -0.0850   0.5904   1.0000
   6.250   0.9726   0.01929   0.01233  -0.0863   0.5419   1.0000
   6.500   1.0029   0.01990   0.01265  -0.0870   0.4971   1.0000
   6.750   1.0317   0.02070   0.01318  -0.0877   0.4590   1.0000
   7.000   1.0602   0.02157   0.01387  -0.0884   0.4279   1.0000
   7.250   1.0929   0.02249   0.01458  -0.0899   0.4029   1.0000
   7.500   1.1228   0.02339   0.01549  -0.0909   0.3818   1.0000
   7.750   1.1559   0.02432   0.01637  -0.0925   0.3641   1.0000
   8.000   1.1911   0.02529   0.01734  -0.0945   0.3495   1.0000
   8.250   1.2270   0.02631   0.01840  -0.0966   0.3370   1.0000
   8.500   1.2632   0.02736   0.01951  -0.0988   0.3256   1.0000
   8.750   1.3053   0.02850   0.02069  -0.1020   0.3153   1.0000
   9.000   1.3333   0.02956   0.02202  -0.1027   0.3062   1.0000
   9.250   1.3642   0.03065   0.02325  -0.1040   0.2963   1.0000
   9.500   1.3833   0.03138   0.02405  -0.1032   0.2833   1.0000
   9.750   1.3897   0.03188   0.02461  -0.1005   0.2684   1.0000
  10.000   1.3882   0.03238   0.02519  -0.0966   0.2529   1.0000
  10.250   1.3838   0.03303   0.02594  -0.0926   0.2370   1.0000
  10.500   1.3812   0.03392   0.02695  -0.0892   0.2213   1.0000
  10.750   1.3799   0.03503   0.02823  -0.0862   0.2052   1.0000
  11.000   1.3746   0.03649   0.02991  -0.0831   0.1829   1.0000
  11.250   1.3607   0.03916   0.03235  -0.0797   0.1028   1.0000
  11.500   1.3415   0.04387   0.03637  -0.0764   0.0527   1.0000
  11.750   1.3339   0.04770   0.04024  -0.0743   0.0429   1.0000
  12.000   1.3280   0.05142   0.04412  -0.0728   0.0384   1.0000
  12.250   1.3181   0.05566   0.04851  -0.0715   0.0361   1.0000
  12.500   1.3149   0.05942   0.05253  -0.0709   0.0342   1.0000
  12.750   1.3107   0.06349   0.05681  -0.0706   0.0327   1.0000
  13.000   1.3063   0.06772   0.06122  -0.0707   0.0315   1.0000
  13.250   1.3028   0.07200   0.06566  -0.0710   0.0304   1.0000
  13.500   1.3004   0.07624   0.07000  -0.0715   0.0293   1.0000
  13.750   1.2999   0.08024   0.07404  -0.0717   0.0280   1.0000
  14.000   1.3088   0.08319   0.07703  -0.0710   0.0266   1.0000
  14.250   1.3136   0.08687   0.08094  -0.0717   0.0256   1.0000
  14.500   1.3194   0.09050   0.08478  -0.0724   0.0248   1.0000
  14.750   1.3253   0.09421   0.08870  -0.0730   0.0242   1.0000
  15.000   1.3294   0.09834   0.09305  -0.0738   0.0239   1.0000
  15.250   1.3301   0.10300   0.09797  -0.0751   0.0238   1.0000
  15.500   1.3266   0.10834   0.10357  -0.0772   0.0237   1.0000
  15.750   1.3196   0.11434   0.10985  -0.0800   0.0238   1.0000
  16.000   1.3100   0.12093   0.11671  -0.0836   0.0240   1.0000
  16.250   1.2976   0.12819   0.12424  -0.0882   0.0241   1.0000
  16.500   1.2837   0.13608   0.13239  -0.0936   0.0243   1.0000
  16.750   1.2679   0.14479   0.14134  -0.0999   0.0246   1.0000
  17.000   1.2519   0.15401   0.15079  -0.1070   0.0249   1.0000
  17.250   1.2327   0.16452   0.16150  -0.1152   0.0253   1.0000
  17.500   1.2161   0.17500   0.17213  -0.1233   0.0258   1.0000
  17.750   1.1974   0.18682   0.18407  -0.1323   0.0263   1.0000
  18.000   1.1847   0.19747   0.19475  -0.1398   0.0269   1.0000
  18.250   0.8077   0.20596   0.20355  -0.1123   0.0439   1.0000
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