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E387 (e387-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 500,000
Max Cl/Cd: 116.26 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e387-il-500000.txt
Download as CSV file: xf-e387-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2755   0.09944   0.09734  -0.0275   1.0000   0.0161
  -9.750  -0.2761   0.09551   0.09343  -0.0297   1.0000   0.0164
  -9.500  -0.2740   0.09170   0.08964  -0.0313   1.0000   0.0165
  -9.250  -0.2715   0.08789   0.08584  -0.0327   1.0000   0.0166
  -9.000  -0.2697   0.08401   0.08199  -0.0340   1.0000   0.0166
  -8.750  -0.2681   0.08010   0.07810  -0.0353   1.0000   0.0167
  -8.500  -0.2668   0.07627   0.07429  -0.0365   1.0000   0.0167
  -8.250  -0.2709   0.07122   0.06928  -0.0366   1.0000   0.0172
  -8.000  -0.2685   0.06812   0.06621  -0.0369   1.0000   0.0175
  -7.750  -0.2649   0.06476   0.06288  -0.0380   0.9965   0.0177
  -7.500  -0.2490   0.06005   0.05816  -0.0428   0.9732   0.0183
  -7.250  -0.2338   0.05491   0.05299  -0.0485   0.9442   0.0190
  -7.000  -0.2326   0.05092   0.04891  -0.0512   0.9027   0.0192
  -6.750  -0.2345   0.04716   0.04505  -0.0537   0.8719   0.0197
  -6.500  -0.2321   0.04249   0.04027  -0.0582   0.8495   0.0203
  -6.250  -0.2252   0.03708   0.03473  -0.0634   0.8320   0.0210
  -5.750  -0.1959   0.03910   0.03595  -0.0814   0.8468   0.0226
  -5.500  -0.1869   0.03291   0.02951  -0.0832   0.8293   0.0239
  -5.250  -0.1664   0.03132   0.02777  -0.0834   0.8137   0.0250
  -5.000  -0.1439   0.02900   0.02519  -0.0837   0.7997   0.0273
  -4.750  -0.1204   0.02501   0.02047  -0.0839   0.7876   0.0316
  -4.500  -0.0971   0.02304   0.01842  -0.0841   0.7759   0.0331
  -4.250  -0.0721   0.02166   0.01684  -0.0840   0.7655   0.0353
  -4.000  -0.0441   0.01475   0.00875  -0.0824   0.7570   0.0189
  -3.750  -0.0164   0.01341   0.00704  -0.0817   0.7476   0.0171
  -3.500   0.0106   0.01269   0.00615  -0.0814   0.7390   0.0168
  -3.250   0.0376   0.01174   0.00508  -0.0811   0.7301   0.0168
  -3.000   0.0640   0.01075   0.00395  -0.0807   0.7224   0.0174
  -2.750   0.0912   0.01019   0.00332  -0.0806   0.7143   0.0187
  -2.500   0.1189   0.00987   0.00291  -0.0804   0.7070   0.0207
  -2.250   0.1467   0.00957   0.00253  -0.0803   0.6996   0.0237
  -2.000   0.1744   0.00921   0.00217  -0.0801   0.6930   0.0423
  -1.750   0.2016   0.00871   0.00199  -0.0802   0.6859   0.1316
  -1.500   0.2288   0.00840   0.00189  -0.0803   0.6799   0.2173
  -1.250   0.2557   0.00795   0.00185  -0.0804   0.6731   0.3486
  -1.000   0.2815   0.00746   0.00184  -0.0802   0.6673   0.5223
  -0.750   0.3054   0.00689   0.00188  -0.0794   0.6611   0.7155
  -0.500   0.3249   0.00646   0.00190  -0.0771   0.6554   0.8836
  -0.250   0.3698   0.00636   0.00179  -0.0805   0.6495   1.0000
   0.000   0.3973   0.00642   0.00177  -0.0804   0.6435   1.0000
   0.250   0.4246   0.00652   0.00175  -0.0802   0.6381   1.0000
   0.500   0.4523   0.00657   0.00176  -0.0802   0.6322   1.0000
   0.750   0.4799   0.00665   0.00176  -0.0801   0.6267   1.0000
   1.000   0.5075   0.00675   0.00179  -0.0800   0.6214   1.0000
   1.250   0.5352   0.00681   0.00182  -0.0800   0.6155   1.0000
   1.500   0.5628   0.00691   0.00185  -0.0799   0.6102   1.0000
   1.750   0.5905   0.00699   0.00192  -0.0798   0.6044   1.0000
   2.000   0.6181   0.00706   0.00196  -0.0798   0.5984   1.0000
   2.250   0.6456   0.00717   0.00202  -0.0797   0.5925   1.0000
   2.500   0.6732   0.00723   0.00208  -0.0796   0.5856   1.0000
   2.750   0.7006   0.00735   0.00216  -0.0795   0.5791   1.0000
   3.000   0.7281   0.00740   0.00223  -0.0795   0.5713   1.0000
   3.250   0.7553   0.00752   0.00230  -0.0794   0.5644   1.0000
   3.500   0.7828   0.00758   0.00239  -0.0793   0.5563   1.0000
   3.750   0.8100   0.00769   0.00250  -0.0792   0.5487   1.0000
   4.000   0.8372   0.00777   0.00260  -0.0790   0.5400   1.0000
   4.250   0.8644   0.00787   0.00271  -0.0789   0.5311   1.0000
   4.500   0.8913   0.00799   0.00282  -0.0788   0.5217   1.0000
   4.750   0.9183   0.00808   0.00296  -0.0786   0.5113   1.0000
   5.000   0.9450   0.00820   0.00309  -0.0784   0.4982   1.0000
   5.250   0.9708   0.00835   0.00320  -0.0781   0.4750   1.0000
   5.500   0.9961   0.00857   0.00335  -0.0777   0.4474   1.0000
   5.750   1.0213   0.00883   0.00357  -0.0773   0.4217   1.0000
   6.000   1.0454   0.00921   0.00383  -0.0768   0.3840   1.0000
   6.250   1.0660   0.00997   0.00426  -0.0759   0.3148   1.0000
   6.500   1.0838   0.01105   0.00492  -0.0747   0.2350   1.0000
   6.750   1.1018   0.01212   0.00563  -0.0735   0.1679   1.0000
   7.000   1.1190   0.01323   0.00639  -0.0723   0.1069   1.0000
   7.250   1.1337   0.01456   0.00732  -0.0707   0.0462   1.0000
   7.500   1.1498   0.01571   0.00828  -0.0691   0.0194   1.0000
   7.750   1.1705   0.01635   0.00900  -0.0681   0.0169   1.0000
   8.000   1.1893   0.01714   0.00984  -0.0668   0.0151   1.0000
   8.250   1.2061   0.01806   0.01087  -0.0652   0.0141   1.0000
   8.500   1.2241   0.01881   0.01171  -0.0639   0.0135   1.0000
   8.750   1.2395   0.01970   0.01269  -0.0622   0.0131   1.0000
   9.000   1.2535   0.02064   0.01372  -0.0604   0.0127   1.0000
   9.250   1.2641   0.02168   0.01487  -0.0580   0.0124   1.0000
   9.500   1.2712   0.02275   0.01602  -0.0552   0.0120   1.0000
   9.750   1.2773   0.02394   0.01729  -0.0525   0.0118   1.0000
  10.000   1.2827   0.02526   0.01872  -0.0499   0.0117   1.0000
  10.250   1.2879   0.02674   0.02027  -0.0477   0.0114   1.0000
  10.500   1.2932   0.02836   0.02200  -0.0456   0.0114   1.0000
  10.750   1.2985   0.03012   0.02384  -0.0438   0.0111   1.0000
  11.000   1.3049   0.03197   0.02578  -0.0421   0.0110   1.0000
  11.250   1.3125   0.03386   0.02779  -0.0406   0.0110   1.0000
  11.500   1.3206   0.03591   0.02996  -0.0392   0.0108   1.0000
  11.750   1.3291   0.03824   0.03240  -0.0379   0.0106   1.0000
  12.000   1.3393   0.04141   0.03574  -0.0366   0.0103   1.0000
  12.250   1.3467   0.04359   0.03807  -0.0355   0.0103   1.0000
  12.500   1.3516   0.04632   0.04099  -0.0344   0.0103   1.0000
  12.750   1.3536   0.04922   0.04409  -0.0335   0.0104   1.0000
  13.000   1.3536   0.05204   0.04709  -0.0327   0.0104   1.0000
  13.250   1.3506   0.05530   0.05055  -0.0322   0.0105   1.0000
  13.500   1.3452   0.05887   0.05432  -0.0319   0.0105   1.0000
  13.750   1.3354   0.06304   0.05880  -0.0320   0.0109   1.0000
  14.000   1.2859   0.07440   0.07086  -0.0336   0.0125   1.0000
  14.250   1.2621   0.08158   0.07828  -0.0358   0.0130   1.0000
  14.500   1.2408   0.08850   0.08540  -0.0386   0.0132   1.0000
  14.750   1.2188   0.09609   0.09316  -0.0422   0.0135   1.0000
  15.000   1.0686   0.10057   0.09795  -0.0423   0.0120   1.0000
  15.250   1.0383   0.10856   0.10615  -0.0471   0.0122   1.0000
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