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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 100,000
Max Cl/Cd: 59.73 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e853-il-100000-n5.txt
Download as CSV file: xf-e853-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 AIRFOIL                             
  
 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  -0.4063   0.09170   0.08685  -0.0485   1.0000   0.0179
  -9.250  -0.4129   0.08720   0.08244  -0.0497   1.0000   0.0171
  -9.000  -0.4220   0.08245   0.07779  -0.0512   1.0000   0.0179
  -8.750  -0.4340   0.07733   0.07277  -0.0527   1.0000   0.0172
  -8.250  -0.5049   0.06214   0.05754  -0.0574   1.0000   0.0133
  -8.000  -0.5259   0.05918   0.05456  -0.0568   1.0000   0.0132
  -7.750  -0.5156   0.05259   0.04761  -0.0650   0.9909   0.0131
  -7.500  -0.5018   0.04592   0.04045  -0.0721   0.9816   0.0139
  -7.250  -0.4814   0.04230   0.03652  -0.0758   0.9729   0.0148
  -7.000  -0.4574   0.03927   0.03313  -0.0787   0.9651   0.0161
  -6.750  -0.4302   0.03554   0.02887  -0.0815   0.9585   0.0171
  -6.500  -0.4044   0.03207   0.02486  -0.0829   0.9508   0.0176
  -6.250  -0.3729   0.02901   0.02127  -0.0846   0.9457   0.0186
  -6.000  -0.3443   0.02668   0.01856  -0.0852   0.9390   0.0198
  -5.750  -0.3123   0.02485   0.01641  -0.0862   0.9337   0.0215
  -5.500  -0.2815   0.02320   0.01467  -0.0877   0.9284   0.0267
  -5.250  -0.2516   0.02182   0.01309  -0.0883   0.9218   0.0318
  -5.000  -0.2169   0.02051   0.01171  -0.0902   0.9179   0.0442
  -4.750  -0.1883   0.01936   0.01058  -0.0911   0.9104   0.0621
  -4.500  -0.1533   0.01821   0.00948  -0.0932   0.9058   0.0976
  -4.250  -0.1210   0.01699   0.00855  -0.0951   0.8999   0.1696
  -4.000  -0.0905   0.01568   0.00816  -0.0970   0.8939   0.3723
  -3.750  -0.0549   0.01554   0.00804  -0.0984   0.8898   0.4650
  -3.500  -0.0266   0.01557   0.00798  -0.0984   0.8816   0.5034
  -3.250   0.0083   0.01555   0.00782  -0.0995   0.8770   0.5334
  -3.000   0.0366   0.01561   0.00778  -0.0994   0.8694   0.5585
  -2.750   0.0696   0.01561   0.00765  -0.1002   0.8642   0.5830
  -2.500   0.0986   0.01561   0.00756  -0.1003   0.8573   0.5987
  -2.250   0.1309   0.01553   0.00734  -0.1012   0.8515   0.6104
  -2.000   0.1617   0.01545   0.00717  -0.1018   0.8455   0.6196
  -1.750   0.1917   0.01539   0.00700  -0.1022   0.8390   0.6282
  -1.500   0.2249   0.01531   0.00680  -0.1034   0.8340   0.6377
  -1.250   0.2517   0.01530   0.00676  -0.1032   0.8267   0.6456
  -1.000   0.2843   0.01523   0.00660  -0.1042   0.8219   0.6544
  -0.750   0.3110   0.01527   0.00660  -0.1041   0.8148   0.6636
  -0.500   0.3412   0.01524   0.00655  -0.1046   0.8096   0.6721
  -0.250   0.3692   0.01527   0.00656  -0.1047   0.8035   0.6815
   0.000   0.3975   0.01529   0.00657  -0.1049   0.7975   0.6915
   0.250   0.4273   0.01529   0.00657  -0.1052   0.7928   0.7011
   0.500   0.4523   0.01538   0.00670  -0.1048   0.7860   0.7115
   0.750   0.4821   0.01539   0.00673  -0.1052   0.7813   0.7230
   1.000   0.5077   0.01550   0.00689  -0.1049   0.7751   0.7351
   1.250   0.5349   0.01556   0.00700  -0.1048   0.7696   0.7479
   1.500   0.5629   0.01561   0.00711  -0.1048   0.7648   0.7617
   1.750   0.5865   0.01573   0.00734  -0.1040   0.7584   0.7768
   2.000   0.6139   0.01576   0.00748  -0.1038   0.7537   0.7935
   2.250   0.6364   0.01588   0.00773  -0.1028   0.7474   0.8131
   2.500   0.6608   0.01593   0.00790  -0.1020   0.7418   0.8364
   2.750   0.6847   0.01596   0.00806  -0.1010   0.7365   0.8664
   3.000   0.7086   0.01600   0.00831  -0.1001   0.7297   0.9123
   3.250   0.7460   0.01597   0.00837  -0.1021   0.7245   1.0000
   3.500   0.7710   0.01624   0.00872  -0.1019   0.7160   1.0000
   3.750   0.8004   0.01638   0.00890  -0.1023   0.7086   1.0000
   4.000   0.8279   0.01652   0.00916  -0.1022   0.6995   1.0000
   4.250   0.8535   0.01664   0.00938  -0.1018   0.6883   1.0000
   4.500   0.8798   0.01666   0.00947  -0.1012   0.6747   1.0000
   4.750   0.9061   0.01658   0.00944  -0.1004   0.6578   1.0000
   5.000   0.9293   0.01658   0.00953  -0.0992   0.6385   1.0000
   5.250   0.9522   0.01662   0.00972  -0.0980   0.6181   1.0000
   5.500   0.9743   0.01670   0.00991  -0.0966   0.5957   1.0000
   5.750   0.9949   0.01681   0.01011  -0.0949   0.5672   1.0000
   6.000   1.0136   0.01697   0.01028  -0.0929   0.5263   1.0000
   6.250   1.0292   0.01732   0.01041  -0.0902   0.4548   1.0000
   6.500   1.0344   0.01840   0.01083  -0.0862   0.3498   1.0000
   6.750   1.0352   0.01998   0.01182  -0.0820   0.2567   1.0000
   7.000   1.0386   0.02153   0.01292  -0.0785   0.1854   1.0000
   7.250   1.0436   0.02295   0.01402  -0.0753   0.1356   1.0000
   7.500   1.0511   0.02423   0.01514  -0.0725   0.1040   1.0000
   7.750   1.0587   0.02558   0.01643  -0.0697   0.0820   1.0000
   8.000   1.0675   0.02689   0.01772  -0.0672   0.0638   1.0000
   8.250   1.0754   0.02832   0.01915  -0.0647   0.0519   1.0000
   8.500   1.0834   0.02980   0.02064  -0.0623   0.0419   1.0000
   8.750   1.0898   0.03147   0.02235  -0.0599   0.0353   1.0000
   9.000   1.0985   0.03308   0.02408  -0.0577   0.0295   1.0000
   9.250   1.1054   0.03489   0.02594  -0.0557   0.0249   1.0000
   9.500   1.1135   0.03699   0.02817  -0.0536   0.0223   1.0000
   9.750   1.1251   0.03868   0.03003  -0.0521   0.0189   1.0000
  10.000   1.1338   0.04051   0.03193  -0.0507   0.0167   1.0000
  10.250   1.1438   0.04338   0.03492  -0.0491   0.0153   1.0000
  10.500   1.1593   0.04587   0.03771  -0.0478   0.0145   1.0000
  10.750   1.1726   0.04878   0.04103  -0.0465   0.0137   1.0000
  11.000   1.1805   0.05178   0.04436  -0.0450   0.0130   1.0000
  11.250   1.1831   0.05474   0.04764  -0.0435   0.0122   1.0000
  11.500   1.1819   0.05772   0.05090  -0.0422   0.0115   1.0000
  11.750   1.1781   0.06093   0.05437  -0.0410   0.0110   1.0000
  12.000   1.1722   0.06425   0.05792  -0.0402   0.0105   1.0000
  12.250   1.1645   0.06790   0.06179  -0.0398   0.0102   1.0000
  12.500   1.1548   0.07195   0.06606  -0.0398   0.0099   1.0000
  12.750   1.1421   0.07676   0.07113  -0.0402   0.0098   1.0000
  13.000   1.1280   0.08191   0.07652  -0.0413   0.0097   1.0000
  13.250   1.1117   0.08772   0.08258  -0.0430   0.0097   1.0000
  13.500   1.0937   0.09424   0.08934  -0.0456   0.0098   1.0000
  13.750   1.0723   0.10207   0.09744  -0.0494   0.0099   1.0000
  14.000   1.0420   0.11315   0.10883  -0.0558   0.0105   1.0000
  14.250   0.9982   0.13064   0.12659  -0.0670   0.0121   1.0000
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