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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 100,000
Max Cl/Cd: 45.28 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e186-il-100000-n5.txt
Download as CSV file: xf-e186-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6629   0.08872   0.08453   0.0142   1.0000   0.0265
  -9.250  -0.6768   0.08010   0.07597   0.0069   1.0000   0.0258
  -9.000  -0.7000   0.07140   0.06721   0.0008   1.0000   0.0251
  -8.750  -0.7250   0.06476   0.06040  -0.0003   1.0000   0.0245
  -8.500  -0.7446   0.05816   0.05346  -0.0002   1.0000   0.0240
  -8.250  -0.7509   0.05313   0.04807   0.0008   1.0000   0.0238
  -8.000  -0.7504   0.04872   0.04329   0.0020   1.0000   0.0238
  -7.750  -0.7434   0.04527   0.03953   0.0031   1.0000   0.0242
  -7.500  -0.7299   0.04301   0.03710   0.0038   1.0000   0.0254
  -7.250  -0.7166   0.04024   0.03400   0.0049   1.0000   0.0266
  -7.000  -0.7022   0.03709   0.03042   0.0061   1.0000   0.0274
  -6.750  -0.6852   0.03392   0.02677   0.0073   1.0000   0.0276
  -6.500  -0.6648   0.03116   0.02358   0.0081   1.0000   0.0278
  -6.250  -0.6383   0.02868   0.02069   0.0081   0.9482   0.0282
  -6.000  -0.6113   0.02672   0.01831   0.0084   0.9021   0.0289
  -5.750  -0.5894   0.02523   0.01646   0.0099   0.8715   0.0296
  -5.500  -0.5679   0.02395   0.01491   0.0115   0.8479   0.0304
  -5.250  -0.5461   0.02297   0.01367   0.0130   0.8283   0.0317
  -5.000  -0.5257   0.02178   0.01244   0.0144   0.8113   0.0346
  -4.750  -0.5037   0.02096   0.01148   0.0156   0.7964   0.0373
  -4.500  -0.4816   0.02012   0.01046   0.0170   0.7829   0.0395
  -4.250  -0.4591   0.01940   0.00952   0.0183   0.7706   0.0421
  -4.000  -0.4370   0.01859   0.00857   0.0196   0.7597   0.0473
  -3.750  -0.4137   0.01783   0.00777   0.0206   0.7487   0.0607
  -3.500  -0.3909   0.01699   0.00712   0.0215   0.7385   0.1079
  -3.250  -0.3692   0.01607   0.00668   0.0224   0.7294   0.2069
  -3.000  -0.3488   0.01507   0.00634   0.0235   0.7205   0.3471
  -2.750  -0.3295   0.01390   0.00612   0.0252   0.7119   0.5475
  -2.500  -0.2905   0.01315   0.00605   0.0242   0.7043   0.7456
  -2.250  -0.2186   0.01333   0.00623   0.0169   0.6948   0.8559
  -2.000  -0.1720   0.01362   0.00627   0.0140   0.6869   0.8989
  -1.750  -0.1331   0.01390   0.00633   0.0124   0.6788   0.9284
  -1.500  -0.0916   0.01412   0.00635   0.0099   0.6710   0.9501
  -1.250  -0.0511   0.01430   0.00630   0.0075   0.6636   0.9693
  -1.000  -0.0052   0.01435   0.00618   0.0038   0.6559   0.9842
  -0.750   0.0414   0.01425   0.00590  -0.0002   0.6487   0.9965
  -0.500   0.0726   0.01418   0.00571  -0.0013   0.6414   1.0000
  -0.250   0.0961   0.01416   0.00557  -0.0007   0.6351   1.0000
   0.000   0.1205   0.01417   0.00549  -0.0003   0.6283   1.0000
   0.250   0.1447   0.01418   0.00542   0.0002   0.6219   1.0000
   0.500   0.1693   0.01422   0.00539   0.0006   0.6157   1.0000
   0.750   0.1941   0.01426   0.00538   0.0010   0.6091   1.0000
   1.000   0.2186   0.01432   0.00536   0.0015   0.6036   1.0000
   1.250   0.2440   0.01439   0.00544   0.0018   0.5966   1.0000
   1.500   0.2686   0.01447   0.00545   0.0024   0.5913   1.0000
   1.750   0.2942   0.01458   0.00559   0.0026   0.5844   1.0000
   2.000   0.3191   0.01467   0.00568   0.0031   0.5785   1.0000
   2.250   0.3446   0.01480   0.00583   0.0034   0.5722   1.0000
   2.500   0.3698   0.01493   0.00597   0.0038   0.5657   1.0000
   2.750   0.3949   0.01506   0.00612   0.0042   0.5597   1.0000
   3.000   0.4204   0.01520   0.00635   0.0046   0.5525   1.0000
   3.250   0.4454   0.01534   0.00651   0.0051   0.5461   1.0000
   3.500   0.4708   0.01548   0.00673   0.0054   0.5380   1.0000
   3.750   0.4960   0.01561   0.00692   0.0059   0.5299   1.0000
   4.000   0.5208   0.01571   0.00707   0.0065   0.5215   1.0000
   4.250   0.5462   0.01584   0.00735   0.0069   0.5112   1.0000
   4.500   0.5711   0.01593   0.00753   0.0075   0.5010   1.0000
   4.750   0.5959   0.01600   0.00766   0.0082   0.4902   1.0000
   5.000   0.6207   0.01606   0.00781   0.0089   0.4779   1.0000
   5.250   0.6455   0.01613   0.00800   0.0095   0.4638   1.0000
   5.500   0.6705   0.01623   0.00829   0.0100   0.4470   1.0000
   5.750   0.6952   0.01633   0.00853   0.0106   0.4276   1.0000
   6.000   0.7196   0.01644   0.00874   0.0112   0.4051   1.0000
   6.250   0.7438   0.01663   0.00902   0.0119   0.3753   1.0000
   6.500   0.7671   0.01694   0.00933   0.0125   0.3340   1.0000
   6.750   0.7888   0.01756   0.00983   0.0131   0.2772   1.0000
   7.000   0.8079   0.01868   0.01065   0.0136   0.2125   1.0000
   7.250   0.8237   0.02032   0.01187   0.0140   0.1429   1.0000
   7.500   0.8377   0.02205   0.01315   0.0146   0.0841   1.0000
   7.750   0.8521   0.02356   0.01448   0.0156   0.0537   1.0000
   8.000   0.8649   0.02516   0.01606   0.0169   0.0371   1.0000
   8.250   0.8753   0.02688   0.01782   0.0185   0.0302   1.0000
   8.500   0.8864   0.02835   0.01940   0.0200   0.0256   1.0000
   8.750   0.8929   0.03010   0.02125   0.0217   0.0229   1.0000
   9.000   0.9021   0.03152   0.02282   0.0235   0.0208   1.0000
   9.250   0.9085   0.03312   0.02455   0.0254   0.0195   1.0000
   9.500   0.9138   0.03478   0.02633   0.0272   0.0186   1.0000
   9.750   0.9161   0.03643   0.02806   0.0293   0.0181   1.0000
  10.000   0.9175   0.03827   0.02998   0.0312   0.0175   1.0000
  10.250   0.9206   0.04022   0.03202   0.0327   0.0170   1.0000
  10.500   0.9247   0.04235   0.03424   0.0341   0.0166   1.0000
  10.750   0.9289   0.04485   0.03684   0.0355   0.0161   1.0000
  11.000   0.9333   0.04729   0.03949   0.0365   0.0159   1.0000
  11.250   0.9354   0.04996   0.04238   0.0372   0.0158   1.0000
  11.500   0.9342   0.05305   0.04572   0.0376   0.0156   1.0000
  11.750   0.9302   0.05644   0.04934   0.0376   0.0155   1.0000
  12.000   0.9238   0.06014   0.05327   0.0371   0.0155   1.0000
  12.250   0.9142   0.06432   0.05767   0.0360   0.0154   1.0000
  12.500   0.9026   0.06892   0.06249   0.0345   0.0153   1.0000
  12.750   0.8893   0.07392   0.06769   0.0323   0.0152   1.0000
  13.000   0.8750   0.07937   0.07331   0.0297   0.0154   1.0000
  13.250   0.8592   0.08537   0.07948   0.0266   0.0155   1.0000
  13.500   0.8413   0.09216   0.08642   0.0228   0.0155   1.0000
  13.750   0.8230   0.09968   0.09407   0.0185   0.0157   1.0000
  14.000   0.8053   0.10776   0.10226   0.0138   0.0158   1.0000
  14.250   0.7882   0.11636   0.11093   0.0090   0.0160   1.0000
  14.500   0.7705   0.12583   0.12044   0.0040   0.0162   1.0000
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