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E387 (e387-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 200,000
Max Cl/Cd: 84.35 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e387-il-200000.txt
Download as CSV file: xf-e387-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E387                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2667   0.09393   0.09074  -0.0316   1.0000   0.0394
  -9.000  -0.2708   0.09096   0.08781  -0.0345   1.0000   0.0400
  -8.750  -0.2727   0.08774   0.08463  -0.0368   1.0000   0.0403
  -8.500  -0.2740   0.08442   0.08136  -0.0386   1.0000   0.0404
  -8.250  -0.2755   0.08102   0.07802  -0.0403   1.0000   0.0405
  -8.000  -0.2713   0.07486   0.07190  -0.0386   1.0000   0.0416
  -7.750  -0.2637   0.07168   0.06876  -0.0372   1.0000   0.0426
  -7.500  -0.2620   0.06891   0.06605  -0.0363   1.0000   0.0437
  -7.250  -0.2742   0.06743   0.06471  -0.0336   1.0000   0.0443
  -7.000  -0.3570   0.07594   0.07304  -0.0424   1.0000   0.0413
  -6.750  -0.3559   0.07384   0.07100  -0.0392   0.9977   0.0422
  -6.500  -0.3270   0.06980   0.06694  -0.0438   0.9898   0.0441
  -6.250  -0.2923   0.06430   0.06137  -0.0537   0.9798   0.0471
  -6.000  -0.2352   0.05551   0.05197  -0.0765   0.9640   0.0524
  -5.750  -0.2153   0.04957   0.04624  -0.0785   0.9563   0.0549
  -5.500  -0.1851   0.04671   0.04331  -0.0817   0.9439   0.0601
  -5.250  -0.1536   0.04074   0.03688  -0.0886   0.9282   0.0676
  -5.000  -0.1298   0.03822   0.03430  -0.0894   0.9131   0.0707
  -4.750  -0.1051   0.03475   0.03025  -0.0914   0.8964   0.0806
  -4.500  -0.0839   0.03235   0.02783  -0.0911   0.8823   0.0834
  -4.250  -0.0602   0.03008   0.02508  -0.0914   0.8687   0.0949
  -4.000  -0.0274   0.02029   0.01380  -0.0897   0.8583   0.0346
  -3.750  -0.0006   0.01802   0.01092  -0.0887   0.8466   0.0323
  -3.500   0.0256   0.01663   0.00925  -0.0880   0.8358   0.0324
  -3.250   0.0518   0.01553   0.00797  -0.0873   0.8260   0.0336
  -3.000   0.0782   0.01494   0.00728  -0.0868   0.8152   0.0377
  -2.750   0.1049   0.01430   0.00649  -0.0862   0.8055   0.0405
  -2.500   0.1305   0.01327   0.00541  -0.0856   0.7973   0.0466
  -2.250   0.1570   0.01231   0.00459  -0.0851   0.7876   0.0881
  -2.000   0.1824   0.01149   0.00430  -0.0850   0.7796   0.2303
  -1.750   0.2059   0.01064   0.00426  -0.0846   0.7712   0.4548
  -1.500   0.2245   0.00983   0.00430  -0.0824   0.7634   0.7077
  -1.250   0.2697   0.00923   0.00404  -0.0845   0.7563   0.9956
  -1.000   0.2972   0.00934   0.00394  -0.0845   0.7485   1.0000
  -0.750   0.3239   0.00945   0.00384  -0.0842   0.7413   1.0000
  -0.500   0.3506   0.00958   0.00381  -0.0840   0.7339   1.0000
  -0.250   0.3775   0.00970   0.00377  -0.0837   0.7269   1.0000
   0.000   0.4044   0.00984   0.00378  -0.0835   0.7199   1.0000
   0.250   0.4314   0.00997   0.00379  -0.0833   0.7132   1.0000
   0.500   0.4584   0.01012   0.00384  -0.0831   0.7067   1.0000
   0.750   0.4855   0.01025   0.00389  -0.0830   0.6998   1.0000
   1.000   0.5127   0.01042   0.00395  -0.0828   0.6940   1.0000
   1.250   0.5397   0.01057   0.00406  -0.0827   0.6868   1.0000
   1.500   0.5671   0.01073   0.00412  -0.0825   0.6814   1.0000
   1.750   0.5939   0.01090   0.00430  -0.0824   0.6742   1.0000
   2.000   0.6213   0.01105   0.00439  -0.0822   0.6683   1.0000
   2.250   0.6482   0.01124   0.00457  -0.0821   0.6617   1.0000
   2.500   0.6753   0.01140   0.00470  -0.0819   0.6552   1.0000
   2.750   0.7024   0.01158   0.00489  -0.0818   0.6488   1.0000
   3.000   0.7292   0.01173   0.00504  -0.0816   0.6416   1.0000
   3.250   0.7562   0.01190   0.00520  -0.0814   0.6348   1.0000
   3.500   0.7829   0.01204   0.00536  -0.0811   0.6269   1.0000
   3.750   0.8097   0.01219   0.00554  -0.0809   0.6191   1.0000
   4.000   0.8365   0.01230   0.00565  -0.0805   0.6109   1.0000
   4.250   0.8627   0.01244   0.00585  -0.0802   0.6019   1.0000
   4.500   0.8899   0.01254   0.00591  -0.0799   0.5941   1.0000
   4.750   0.9157   0.01263   0.00612  -0.0795   0.5836   1.0000
   5.000   0.9417   0.01273   0.00628  -0.0791   0.5733   1.0000
   5.250   0.9680   0.01280   0.00638  -0.0786   0.5630   1.0000
   5.500   0.9940   0.01286   0.00648  -0.0781   0.5517   1.0000
   5.750   1.0194   0.01292   0.00667  -0.0776   0.5388   1.0000
   6.000   1.0445   0.01295   0.00675  -0.0769   0.5233   1.0000
   6.250   1.0680   0.01292   0.00679  -0.0759   0.4989   1.0000
   6.500   1.0908   0.01297   0.00684  -0.0748   0.4684   1.0000
   6.750   1.1126   0.01319   0.00703  -0.0737   0.4294   1.0000
   7.000   1.1332   0.01362   0.00735  -0.0725   0.3830   1.0000
   7.250   1.1481   0.01457   0.00791  -0.0706   0.3037   1.0000
   7.500   1.1588   0.01602   0.00888  -0.0685   0.2213   1.0000
   7.750   1.1671   0.01774   0.01010  -0.0663   0.1415   1.0000
   8.000   1.1667   0.02026   0.01192  -0.0629   0.0532   1.0000
   8.250   1.1733   0.02205   0.01359  -0.0601   0.0365   1.0000
   8.500   1.1835   0.02337   0.01504  -0.0577   0.0322   1.0000
   8.750   1.1921   0.02463   0.01639  -0.0552   0.0299   1.0000
   9.000   1.1958   0.02608   0.01791  -0.0522   0.0283   1.0000
   9.250   1.1953   0.02801   0.01989  -0.0490   0.0271   1.0000
   9.500   1.1998   0.02989   0.02185  -0.0465   0.0264   1.0000
   9.750   1.2102   0.03144   0.02350  -0.0447   0.0257   1.0000
  10.000   1.2222   0.03303   0.02522  -0.0432   0.0250   1.0000
  10.250   1.2345   0.03455   0.02685  -0.0418   0.0236   1.0000
  10.500   1.2495   0.03634   0.02875  -0.0405   0.0229   1.0000
  10.750   1.2665   0.03831   0.03086  -0.0393   0.0224   1.0000
  11.000   1.2846   0.04056   0.03329  -0.0383   0.0221   1.0000
  11.250   1.3019   0.04321   0.03617  -0.0373   0.0220   1.0000
  11.500   1.3147   0.04631   0.03958  -0.0360   0.0221   1.0000
  11.750   1.3190   0.04991   0.04355  -0.0344   0.0224   1.0000
  12.000   1.3154   0.05391   0.04796  -0.0325   0.0230   1.0000
  12.250   1.3066   0.05809   0.05249  -0.0310   0.0235   1.0000
  12.500   1.2946   0.06254   0.05725  -0.0300   0.0240   1.0000
  12.750   1.2801   0.06729   0.06228  -0.0295   0.0245   1.0000
  13.000   1.2639   0.07234   0.06757  -0.0297   0.0249   1.0000
  13.250   1.2461   0.07779   0.07324  -0.0306   0.0253   1.0000
  13.500   1.2269   0.08368   0.07933  -0.0321   0.0256   1.0000
  13.750   1.2069   0.09018   0.08602  -0.0342   0.0260   1.0000
  14.000   1.2096   0.09456   0.09051  -0.0347   0.0273   1.0000
  14.250   1.1750   0.10244   0.09874  -0.0398   0.0283   1.0000
  14.500   1.1416   0.11207   0.10858  -0.0461   0.0286   1.0000
  14.750   1.1116   0.12263   0.11931  -0.0534   0.0287   1.0000
  15.000   1.0142   0.16314   0.15995  -0.0792   0.0386   1.0000
  15.250   1.0394   0.15676   0.15366  -0.0744   0.0366   1.0000
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