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E184 (8.33%) (e184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E184 (8.33%) (e184-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.39 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e184-il-1000000.txt
Download as CSV file: xf-e184-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E184  (8.33%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6836   0.08063   0.07933   0.0201   1.0000   0.0101
  -8.500  -0.6977   0.07396   0.07269   0.0139   1.0000   0.0101
  -8.250  -0.7080   0.06667   0.06534   0.0093   1.0000   0.0101
  -8.000  -0.7149   0.05770   0.05619   0.0055   0.9466   0.0101
  -7.750  -0.7252   0.05177   0.04991   0.0064   0.8900   0.0101
  -7.500  -0.7282   0.04596   0.04374   0.0069   0.8645   0.0101
  -7.250  -0.7253   0.04080   0.03817   0.0078   0.8456   0.0101
  -7.000  -0.7381   0.02974   0.02640   0.0099   0.8311   0.0094
  -6.750  -0.7257   0.02538   0.02139   0.0117   0.8174   0.0106
  -6.250  -0.6872   0.01996   0.01527   0.0139   0.7936   0.0112
  -6.000  -0.6639   0.01842   0.01351   0.0146   0.7830   0.0115
  -5.750  -0.6399   0.01693   0.01178   0.0153   0.7734   0.0117
  -5.500  -0.6154   0.01541   0.01001   0.0161   0.7642   0.0117
  -5.250  -0.5902   0.01429   0.00873   0.0167   0.7556   0.0119
  -5.000  -0.5643   0.01365   0.00799   0.0170   0.7475   0.0125
  -4.750  -0.5387   0.01270   0.00691   0.0176   0.7396   0.0129
  -4.500  -0.5130   0.01191   0.00600   0.0181   0.7325   0.0133
  -4.250  -0.4870   0.01128   0.00526   0.0186   0.7252   0.0139
  -4.000  -0.4607   0.01076   0.00465   0.0190   0.7188   0.0144
  -3.750  -0.4343   0.01028   0.00409   0.0194   0.7120   0.0147
  -3.500  -0.4077   0.00988   0.00359   0.0198   0.7060   0.0150
  -3.250  -0.3807   0.00952   0.00317   0.0200   0.6997   0.0152
  -3.000  -0.3537   0.00922   0.00278   0.0203   0.6938   0.0157
  -2.750  -0.3267   0.00882   0.00227   0.0206   0.6881   0.0169
  -2.500  -0.2993   0.00855   0.00195   0.0209   0.6823   0.0198
  -2.250  -0.2719   0.00835   0.00173   0.0211   0.6769   0.0270
  -2.000  -0.2458   0.00784   0.00149   0.0214   0.6712   0.0948
  -1.750  -0.2195   0.00747   0.00134   0.0216   0.6658   0.1597
  -1.500  -0.1932   0.00708   0.00122   0.0217   0.6606   0.2384
  -1.250  -0.1680   0.00655   0.00110   0.0221   0.6550   0.3573
  -1.000  -0.1427   0.00614   0.00100   0.0224   0.6498   0.4637
  -0.750  -0.1181   0.00564   0.00093   0.0230   0.6445   0.5864
  -0.500  -0.0963   0.00507   0.00086   0.0243   0.6391   0.7346
  -0.250  -0.0702   0.00447   0.00092   0.0252   0.6340   0.9226
   0.000  -0.0148   0.00460   0.00105   0.0194   0.6276   0.9653
   0.250   0.0213   0.00471   0.00109   0.0177   0.6209   0.9764
   0.500   0.0581   0.00479   0.00114   0.0159   0.6131   0.9844
   0.750   0.0995   0.00485   0.00115   0.0130   0.6054   0.9886
   1.000   0.1384   0.00492   0.00117   0.0106   0.5965   0.9932
   1.250   0.1790   0.00494   0.00117   0.0078   0.5882   0.9963
   1.500   0.2189   0.00496   0.00114   0.0051   0.5792   0.9992
   1.750   0.2495   0.00497   0.00113   0.0045   0.5693   1.0000
   2.000   0.2757   0.00498   0.00112   0.0049   0.5600   1.0000
   2.250   0.3021   0.00501   0.00112   0.0052   0.5505   1.0000
   2.500   0.3286   0.00505   0.00114   0.0055   0.5390   1.0000
   2.750   0.3552   0.00509   0.00116   0.0057   0.5262   1.0000
   3.000   0.3818   0.00514   0.00120   0.0060   0.5122   1.0000
   3.250   0.4086   0.00522   0.00124   0.0062   0.4953   1.0000
   3.500   0.4354   0.00534   0.00130   0.0064   0.4690   1.0000
   3.750   0.4622   0.00561   0.00138   0.0064   0.4135   1.0000
   4.000   0.4890   0.00610   0.00156   0.0062   0.3308   1.0000
   4.250   0.5157   0.00686   0.00188   0.0058   0.2248   1.0000
   4.500   0.5421   0.00742   0.00217   0.0056   0.1580   1.0000
   4.750   0.5682   0.00804   0.00249   0.0055   0.0957   1.0000
   5.000   0.5939   0.00878   0.00292   0.0054   0.0327   1.0000
   5.250   0.6197   0.00940   0.00343   0.0055   0.0102   1.0000
   5.500   0.6455   0.00976   0.00385   0.0058   0.0090   1.0000
   5.750   0.6711   0.01017   0.00431   0.0061   0.0082   1.0000
   6.000   0.6962   0.01073   0.00495   0.0065   0.0074   1.0000
   6.250   0.7203   0.01158   0.00592   0.0069   0.0070   1.0000
   6.500   0.7446   0.01221   0.00662   0.0073   0.0068   1.0000
   6.750   0.7686   0.01278   0.00726   0.0078   0.0067   1.0000
   7.000   0.7923   0.01341   0.00797   0.0083   0.0064   1.0000
   7.250   0.8152   0.01416   0.00879   0.0089   0.0059   1.0000
   7.500   0.8370   0.01511   0.00982   0.0097   0.0056   1.0000
   7.750   0.8579   0.01620   0.01101   0.0106   0.0054   1.0000
   8.000   0.8775   0.01761   0.01255   0.0117   0.0054   1.0000
   8.250   0.8953   0.01959   0.01474   0.0131   0.0056   1.0000
   8.500   0.9101   0.02262   0.01808   0.0148   0.0062   1.0000
  18.250   0.6298   0.20218   0.20069  -0.0487   0.0055   1.0000
  18.500   0.6345   0.20546   0.20398  -0.0505   0.0051   1.0000
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