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E387 (e387-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 200,000
Max Cl/Cd: 82.36 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e387-il-200000-n5.txt
Download as CSV file: xf-e387-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3339   0.08673   0.08341  -0.0327   1.0000   0.0249
  -7.750  -0.3337   0.08358   0.08032  -0.0339   1.0000   0.0252
  -7.500  -0.3358   0.08060   0.07742  -0.0347   1.0000   0.0254
  -7.250  -0.3289   0.07449   0.07138  -0.0473   0.9823   0.0272
  -6.750  -0.2415   0.04444   0.04128  -0.0608   0.8734   0.0215
  -6.250  -0.2466   0.04490   0.04116  -0.0773   0.8891   0.0155
  -6.000  -0.2287   0.04034   0.03633  -0.0801   0.8694   0.0151
  -5.750  -0.2104   0.03548   0.03109  -0.0821   0.8517   0.0146
  -5.500  -0.1908   0.03077   0.02589  -0.0832   0.8362   0.0142
  -5.250  -0.1694   0.02661   0.02114  -0.0837   0.8223   0.0138
  -5.000  -0.1462   0.02324   0.01714  -0.0836   0.8097   0.0136
  -4.500  -0.0958   0.01888   0.01174  -0.0829   0.7864   0.0137
  -4.250  -0.0697   0.01746   0.00996  -0.0825   0.7758   0.0140
  -4.000  -0.0435   0.01633   0.00854  -0.0820   0.7661   0.0145
  -3.750  -0.0169   0.01552   0.00751  -0.0816   0.7562   0.0154
  -3.500   0.0093   0.01471   0.00658  -0.0814   0.7471   0.0170
  -3.250   0.0358   0.01409   0.00584  -0.0811   0.7386   0.0181
  -3.000   0.0628   0.01354   0.00515  -0.0808   0.7299   0.0192
  -2.750   0.0899   0.01311   0.00455  -0.0805   0.7223   0.0207
  -2.500   0.1172   0.01269   0.00404  -0.0804   0.7142   0.0239
  -2.250   0.1444   0.01232   0.00363  -0.0802   0.7073   0.0362
  -2.000   0.1715   0.01186   0.00334  -0.0801   0.6997   0.0862
  -1.750   0.1982   0.01147   0.00316  -0.0801   0.6933   0.1574
  -1.500   0.2246   0.01098   0.00306  -0.0802   0.6860   0.2733
  -1.250   0.2506   0.01059   0.00297  -0.0800   0.6800   0.3883
  -1.000   0.2758   0.01013   0.00294  -0.0796   0.6732   0.5284
  -0.750   0.2978   0.00963   0.00294  -0.0781   0.6672   0.6970
  -0.500   0.3216   0.00920   0.00290  -0.0763   0.6615   0.8832
  -0.250   0.3651   0.00912   0.00274  -0.0794   0.6549   1.0000
   0.000   0.3922   0.00922   0.00268  -0.0792   0.6496   1.0000
   0.250   0.4196   0.00930   0.00267  -0.0792   0.6431   1.0000
   0.500   0.4468   0.00941   0.00265  -0.0790   0.6375   1.0000
   0.750   0.4741   0.00951   0.00267  -0.0789   0.6318   1.0000
   1.000   0.5015   0.00961   0.00270  -0.0788   0.6258   1.0000
   1.250   0.5287   0.00974   0.00272  -0.0786   0.6208   1.0000
   1.500   0.5561   0.00984   0.00280  -0.0786   0.6146   1.0000
   1.750   0.5834   0.00995   0.00287  -0.0785   0.6090   1.0000
   2.000   0.6107   0.01008   0.00295  -0.0784   0.6036   1.0000
   2.250   0.6380   0.01020   0.00306  -0.0783   0.5975   1.0000
   2.500   0.6652   0.01034   0.00315  -0.0781   0.5923   1.0000
   2.750   0.6925   0.01046   0.00331  -0.0780   0.5857   1.0000
   3.000   0.7196   0.01059   0.00342  -0.0779   0.5794   1.0000
   3.250   0.7466   0.01072   0.00357  -0.0778   0.5723   1.0000
   3.500   0.7735   0.01085   0.00371  -0.0776   0.5648   1.0000
   3.750   0.8003   0.01098   0.00388  -0.0774   0.5561   1.0000
   4.000   0.8269   0.01112   0.00401  -0.0771   0.5476   1.0000
   4.250   0.8535   0.01125   0.00418  -0.0769   0.5375   1.0000
   4.500   0.8800   0.01139   0.00439  -0.0767   0.5273   1.0000
   4.750   0.9062   0.01154   0.00457  -0.0764   0.5165   1.0000
   5.000   0.9322   0.01170   0.00475  -0.0760   0.5044   1.0000
   5.250   0.9581   0.01186   0.00496  -0.0756   0.4907   1.0000
   5.500   0.9836   0.01205   0.00522  -0.0753   0.4752   1.0000
   5.750   1.0089   0.01225   0.00547  -0.0748   0.4569   1.0000
   6.000   1.0319   0.01256   0.00569  -0.0740   0.4210   1.0000
   6.250   1.0510   0.01320   0.00600  -0.0727   0.3514   1.0000
   6.500   1.0673   0.01422   0.00663  -0.0712   0.2741   1.0000
   6.750   1.0830   0.01538   0.00743  -0.0699   0.2081   1.0000
   7.000   1.0992   0.01650   0.00826  -0.0686   0.1548   1.0000
   7.250   1.1160   0.01754   0.00910  -0.0673   0.1131   1.0000
   7.500   1.1310   0.01871   0.01003  -0.0659   0.0722   1.0000
   7.750   1.1449   0.01992   0.01108  -0.0643   0.0399   1.0000
   8.000   1.1588   0.02109   0.01215  -0.0626   0.0229   1.0000
   8.250   1.1739   0.02210   0.01319  -0.0610   0.0181   1.0000
   8.500   1.1894   0.02301   0.01420  -0.0594   0.0163   1.0000
   8.750   1.2028   0.02403   0.01531  -0.0577   0.0152   1.0000
   9.000   1.2121   0.02519   0.01658  -0.0554   0.0144   1.0000
   9.250   1.2207   0.02630   0.01784  -0.0531   0.0139   1.0000
   9.500   1.2280   0.02754   0.01922  -0.0508   0.0135   1.0000
   9.750   1.2344   0.02891   0.02072  -0.0487   0.0132   1.0000
  10.000   1.2392   0.03050   0.02244  -0.0467   0.0129   1.0000
  10.250   1.2440   0.03221   0.02427  -0.0450   0.0126   1.0000
  10.500   1.2489   0.03401   0.02619  -0.0436   0.0123   1.0000
  10.750   1.2539   0.03589   0.02818  -0.0423   0.0119   1.0000
  11.000   1.2589   0.03786   0.03025  -0.0413   0.0115   1.0000
  11.250   1.2628   0.04001   0.03251  -0.0403   0.0111   1.0000
  11.500   1.2658   0.04236   0.03495  -0.0394   0.0107   1.0000
  11.750   1.2688   0.04486   0.03755  -0.0385   0.0105   1.0000
  12.000   1.2728   0.04738   0.04019  -0.0375   0.0103   1.0000
  12.250   1.2780   0.04984   0.04279  -0.0367   0.0102   1.0000
  12.500   1.2832   0.05231   0.04543  -0.0361   0.0101   1.0000
  12.750   1.2872   0.05502   0.04833  -0.0356   0.0100   1.0000
  13.000   1.2900   0.05792   0.05142  -0.0352   0.0099   1.0000
  13.250   1.2906   0.06114   0.05486  -0.0350   0.0098   1.0000
  13.500   1.2896   0.06462   0.05855  -0.0351   0.0098   1.0000
  13.750   1.2859   0.06851   0.06267  -0.0354   0.0097   1.0000
  14.000   1.2800   0.07277   0.06720  -0.0361   0.0097   1.0000
  14.250   1.2723   0.07741   0.07207  -0.0372   0.0096   1.0000
  14.500   1.2627   0.08248   0.07736  -0.0387   0.0096   1.0000
  14.750   1.2512   0.08810   0.08322  -0.0408   0.0096   1.0000
  15.000   1.2390   0.09408   0.08942  -0.0433   0.0096   1.0000
  15.250   1.2249   0.10069   0.09625  -0.0465   0.0096   1.0000
  15.500   1.2099   0.10787   0.10365  -0.0503   0.0096   1.0000
  15.750   1.1947   0.11550   0.11147  -0.0546   0.0097   1.0000
  16.000   1.1785   0.12378   0.11995  -0.0595   0.0097   1.0000
  16.250   1.1621   0.13263   0.12897  -0.0651   0.0098   1.0000
  16.500   1.1444   0.14248   0.13899  -0.0714   0.0098   1.0000
  16.750   1.1267   0.15304   0.14968  -0.0783   0.0099   1.0000
  17.000   1.1079   0.16487   0.16162  -0.0858   0.0100   1.0000
  17.250   1.0872   0.17837   0.17520  -0.0940   0.0102   1.0000
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