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EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 642 AIRFOIL (e642-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.4 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e642-il-1000000.txt
Download as CSV file: xf-e642-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 642 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2978   0.08306   0.08026  -0.0799   0.7198   0.0140
 -10.750  -0.3068   0.07716   0.07437  -0.0831   0.7172   0.0140
 -10.500  -0.3329   0.06625   0.06349  -0.0915   0.7149   0.0139
 -10.250  -0.3750   0.05669   0.05380  -0.0965   0.7122   0.0136
 -10.000  -0.4060   0.05133   0.04830  -0.0958   0.7096   0.0135
  -9.750  -0.4260   0.04805   0.04492  -0.0933   0.7071   0.0137
  -9.500  -0.4478   0.04484   0.04158  -0.0891   0.7045   0.0138
  -9.250  -0.4626   0.04201   0.03859  -0.0850   0.7021   0.0140
  -8.250  -0.5090   0.02265   0.01713  -0.0655   0.6940   0.0125
  -8.000  -0.4885   0.02173   0.01606  -0.0645   0.6923   0.0123
  -7.750  -0.4678   0.02056   0.01474  -0.0636   0.6906   0.0123
  -7.500  -0.4459   0.01934   0.01337  -0.0628   0.6888   0.0123
  -7.250  -0.4223   0.01863   0.01255  -0.0622   0.6869   0.0122
  -7.000  -0.3986   0.01748   0.01127  -0.0617   0.6851   0.0122
  -6.750  -0.3743   0.01630   0.00998  -0.0613   0.6833   0.0122
  -6.500  -0.3497   0.01533   0.00892  -0.0609   0.6816   0.0123
  -6.250  -0.3265   0.01426   0.00778  -0.0604   0.6796   0.0126
  -6.000  -0.3026   0.01361   0.00711  -0.0599   0.6784   0.0129
  -5.750  -0.2785   0.01308   0.00657  -0.0594   0.6771   0.0132
  -5.500  -0.2544   0.01259   0.00605  -0.0588   0.6755   0.0135
  -5.250  -0.2302   0.01216   0.00559  -0.0583   0.6739   0.0138
  -5.000  -0.2056   0.01178   0.00518  -0.0578   0.6723   0.0143
  -4.750  -0.1807   0.01145   0.00481  -0.0574   0.6708   0.0148
  -4.500  -0.1556   0.01114   0.00447  -0.0570   0.6692   0.0151
  -4.250  -0.1297   0.01091   0.00420  -0.0568   0.6676   0.0155
  -4.000  -0.1050   0.01057   0.00381  -0.0563   0.6658   0.0160
  -3.750  -0.0797   0.01032   0.00352  -0.0560   0.6638   0.0169
  -3.500  -0.0535   0.01009   0.00329  -0.0558   0.6626   0.0179
  -3.250  -0.0269   0.00991   0.00310  -0.0556   0.6612   0.0194
  -3.000  -0.0007   0.00969   0.00289  -0.0554   0.6596   0.0231
  -2.750   0.0238   0.00931   0.00269  -0.0550   0.6579   0.0614
  -2.500   0.0471   0.00884   0.00252  -0.0544   0.6561   0.1404
  -2.250   0.0696   0.00833   0.00237  -0.0538   0.6544   0.2428
  -2.000   0.0896   0.00762   0.00221  -0.0529   0.6527   0.3989
  -1.750   0.1086   0.00683   0.00202  -0.0517   0.6510   0.5779
  -1.500   0.1271   0.00626   0.00216  -0.0500   0.6489   0.7801
  -1.250   0.1556   0.00639   0.00230  -0.0500   0.6474   0.8057
  -1.000   0.1841   0.00652   0.00241  -0.0501   0.6458   0.8189
  -0.750   0.2119   0.00673   0.00264  -0.0499   0.6440   0.8324
  -0.500   0.2401   0.00689   0.00279  -0.0498   0.6421   0.8394
  -0.250   0.2687   0.00699   0.00285  -0.0500   0.6401   0.8447
   0.000   0.2956   0.00717   0.00305  -0.0495   0.6381   0.8506
   0.250   0.3236   0.00734   0.00319  -0.0494   0.6360   0.8564
   0.500   0.3514   0.00747   0.00329  -0.0494   0.6336   0.8608
   0.750   0.3781   0.00758   0.00342  -0.0490   0.6316   0.8643
   1.000   0.4052   0.00767   0.00353  -0.0488   0.6294   0.8684
   1.250   0.4334   0.00775   0.00361  -0.0489   0.6268   0.8722
   1.500   0.4618   0.00776   0.00360  -0.0491   0.6240   0.8747
   1.750   0.4892   0.00772   0.00355  -0.0491   0.6213   0.8762
   2.000   0.5175   0.00775   0.00354  -0.0494   0.6182   0.8771
   2.250   0.5457   0.00772   0.00353  -0.0496   0.6155   0.8779
   2.500   0.5741   0.00768   0.00350  -0.0500   0.6122   0.8786
   2.750   0.6025   0.00765   0.00348  -0.0503   0.6087   0.8794
   3.000   0.6309   0.00763   0.00345  -0.0506   0.6052   0.8801
   3.250   0.6595   0.00763   0.00344  -0.0510   0.6014   0.8807
   3.500   0.6879   0.00759   0.00343  -0.0513   0.5969   0.8813
   3.750   0.7161   0.00757   0.00341  -0.0516   0.5920   0.8821
   4.000   0.7442   0.00758   0.00341  -0.0519   0.5873   0.8827
   4.250   0.7727   0.00755   0.00342  -0.0523   0.5815   0.8832
   4.500   0.8006   0.00755   0.00341  -0.0526   0.5753   0.8837
   4.750   0.8288   0.00755   0.00344  -0.0529   0.5685   0.8842
   5.000   0.8564   0.00757   0.00345  -0.0532   0.5603   0.8848
   5.250   0.8839   0.00761   0.00350  -0.0534   0.5504   0.8854
   5.500   0.9106   0.00767   0.00355  -0.0534   0.5384   0.8861
   5.750   0.9365   0.00777   0.00361  -0.0534   0.5236   0.8867
   6.000   0.9615   0.00792   0.00372  -0.0532   0.5062   0.8872
   6.250   0.9854   0.00812   0.00386  -0.0527   0.4877   0.8877
   6.500   1.0085   0.00836   0.00403  -0.0522   0.4675   0.8881
   6.750   1.0301   0.00866   0.00425  -0.0514   0.4435   0.8886
   7.000   1.0483   0.00906   0.00451  -0.0500   0.4116   0.8893
   7.250   1.0628   0.00956   0.00483  -0.0480   0.3707   0.8902
   7.500   1.0765   0.01007   0.00518  -0.0458   0.3367   0.8911
   7.750   1.0918   0.01048   0.00550  -0.0439   0.3113   0.8922
   8.000   1.1031   0.01095   0.00586  -0.0412   0.2851   0.8933
   8.250   1.1086   0.01148   0.00626  -0.0375   0.2578   0.8945
   8.500   1.1146   0.01209   0.00676  -0.0340   0.2325   0.8958
   8.750   1.1242   0.01264   0.00724  -0.0313   0.2136   0.8970
   9.000   1.1330   0.01324   0.00778  -0.0286   0.1952   0.8982
   9.250   1.1397   0.01397   0.00842  -0.0258   0.1766   0.8995
   9.500   1.1464   0.01476   0.00915  -0.0232   0.1598   0.9008
   9.750   1.1533   0.01562   0.00994  -0.0208   0.1433   0.9020
  10.000   1.1593   0.01661   0.01086  -0.0185   0.1265   0.9031
  10.250   1.1639   0.01772   0.01189  -0.0162   0.1096   0.9046
  10.500   1.1677   0.01893   0.01303  -0.0139   0.0933   0.9065
  10.750   1.1730   0.02013   0.01418  -0.0119   0.0788   0.9082
  11.000   1.1775   0.02145   0.01544  -0.0100   0.0642   0.9098
  11.250   1.1784   0.02304   0.01694  -0.0079   0.0476   0.9115
  11.500   1.1783   0.02477   0.01856  -0.0059   0.0320   0.9133
  11.750   1.1809   0.02638   0.02012  -0.0042   0.0206   0.9150
  12.000   1.1834   0.02806   0.02176  -0.0026   0.0131   0.9166
  12.250   1.1911   0.02942   0.02316  -0.0015   0.0111   0.9180
  12.500   1.1985   0.03080   0.02457  -0.0004   0.0100   0.9200
  12.750   1.2057   0.03222   0.02606   0.0007   0.0094   0.9222
  13.000   1.2144   0.03356   0.02747   0.0015   0.0090   0.9243
  13.250   1.2221   0.03503   0.02901   0.0024   0.0086   0.9267
  13.500   1.2305   0.03648   0.03053   0.0031   0.0084   0.9292
  13.750   1.2377   0.03808   0.03220   0.0038   0.0081   0.9318
  14.000   1.2439   0.03976   0.03396   0.0045   0.0079   0.9356
  14.250   1.2483   0.04163   0.03592   0.0052   0.0076   0.9405
  14.500   1.2522   0.04366   0.03805   0.0058   0.0074   0.9469
  14.750   1.2584   0.04580   0.04030   0.0058   0.0073   0.9584
  15.000   1.2586   0.04935   0.04400   0.0046   0.0070   0.9725
  15.250   1.2638   0.05163   0.04635   0.0044   0.0070   1.0000
  15.500   1.2696   0.05385   0.04865   0.0042   0.0069   1.0000
  15.750   1.2736   0.05633   0.05120   0.0041   0.0068   1.0000
  16.000   1.2774   0.05887   0.05382   0.0038   0.0066   1.0000
  16.250   1.2794   0.06168   0.05671   0.0035   0.0065   1.0000
  16.500   1.2803   0.06468   0.05979   0.0030   0.0064   1.0000
  16.750   1.2806   0.06784   0.06303   0.0025   0.0063   1.0000
  17.000   1.2793   0.07127   0.06655   0.0018   0.0062   1.0000
  17.250   1.2777   0.07481   0.07018   0.0010   0.0061   1.0000
  17.500   1.2767   0.07836   0.07381   0.0000   0.0060   1.0000
  17.750   1.2723   0.08247   0.07801  -0.0012   0.0059   1.0000
  18.000   1.2708   0.08625   0.08188  -0.0024   0.0059   1.0000
  18.250   1.2656   0.09061   0.08634  -0.0039   0.0059   1.0000
  18.500   1.2617   0.09488   0.09070  -0.0054   0.0058   1.0000
  18.750   1.2576   0.09927   0.09517  -0.0071   0.0057   1.0000
  19.000   1.2506   0.10417   0.10017  -0.0091   0.0056   1.0000
  19.250   1.2475   0.10852   0.10461  -0.0110   0.0056   1.0000
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