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EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 682 AIRFOIL (e682-il)
Reynolds number: 500,000
Max Cl/Cd: 91.18 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e682-il-500000.txt
Download as CSV file: xf-e682-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 682 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2097   0.06861   0.06568  -0.0990   0.8202   0.0269
 -10.750  -0.2342   0.06024   0.05724  -0.1049   0.8193   0.0269
 -10.500  -0.2591   0.05435   0.05127  -0.1082   0.8181   0.0269
 -10.250  -0.2827   0.04995   0.04678  -0.1091   0.8166   0.0269
 -10.000  -0.3041   0.04643   0.04316  -0.1084   0.8150   0.0269
  -9.750  -0.3267   0.04352   0.04013  -0.1063   0.8132   0.0269
  -9.500  -0.3494   0.04124   0.03771  -0.1027   0.8113   0.0269
  -9.250  -0.3852   0.03449   0.03082  -0.0987   0.8096   0.0275
  -9.000  -0.3784   0.03200   0.02832  -0.0976   0.8084   0.0279
  -8.750  -0.3742   0.02998   0.02624  -0.0959   0.8069   0.0283
  -8.500  -0.3705   0.02802   0.02419  -0.0939   0.8053   0.0288
  -8.250  -0.3648   0.02601   0.02209  -0.0921   0.8041   0.0295
  -8.000  -0.3592   0.02388   0.01983  -0.0900   0.8028   0.0305
  -7.750  -0.3502   0.02408   0.01963  -0.0865   0.8012   0.0337
  -7.250  -0.3603   0.02394   0.01790  -0.0825   0.8007   0.0203
  -7.000  -0.3386   0.02169   0.01538  -0.0817   0.7995   0.0195
  -6.750  -0.3140   0.02001   0.01349  -0.0812   0.7981   0.0191
  -6.500  -0.2879   0.01874   0.01205  -0.0810   0.7968   0.0189
  -6.250  -0.2620   0.01784   0.01106  -0.0808   0.7956   0.0192
  -6.000  -0.2366   0.01720   0.01035  -0.0806   0.7945   0.0198
  -5.750  -0.2113   0.01648   0.00956  -0.0803   0.7933   0.0202
  -5.500  -0.1870   0.01582   0.00883  -0.0798   0.7921   0.0203
  -5.250  -0.1637   0.01529   0.00825  -0.0792   0.7909   0.0206
  -5.000  -0.1409   0.01489   0.00780  -0.0784   0.7896   0.0211
  -4.750  -0.1195   0.01437   0.00727  -0.0775   0.7882   0.0216
  -4.500  -0.0986   0.01387   0.00675  -0.0765   0.7866   0.0225
  -4.250  -0.0757   0.01354   0.00642  -0.0758   0.7849   0.0239
  -4.000  -0.0518   0.01330   0.00616  -0.0753   0.7831   0.0255
  -3.750  -0.0279   0.01304   0.00588  -0.0747   0.7814   0.0288
  -3.500  -0.0043   0.01274   0.00562  -0.0741   0.7798   0.0396
  -3.250   0.0132   0.01198   0.00535  -0.0727   0.7781   0.1481
  -3.000   0.0302   0.01127   0.00516  -0.0712   0.7765   0.2854
  -2.750   0.0425   0.01040   0.00501  -0.0691   0.7747   0.4754
  -2.500   0.0495   0.00942   0.00513  -0.0652   0.7726   0.7196
  -2.250   0.0741   0.00993   0.00575  -0.0640   0.7705   0.7993
  -2.000   0.1004   0.01033   0.00611  -0.0634   0.7683   0.8181
  -1.750   0.1268   0.01073   0.00647  -0.0627   0.7662   0.8314
  -1.500   0.1520   0.01141   0.00716  -0.0610   0.7642   0.8433
  -1.250   0.1784   0.01177   0.00749  -0.0600   0.7625   0.8507
  -1.000   0.2060   0.01211   0.00778  -0.0594   0.7608   0.8571
  -0.750   0.2324   0.01251   0.00814  -0.0584   0.7589   0.8652
  -0.500   0.2586   0.01284   0.00848  -0.0575   0.7563   0.8717
  -0.250   0.2823   0.01294   0.00857  -0.0566   0.7534   0.8786
   0.000   0.3131   0.01306   0.00867  -0.0568   0.7510   0.8818
   0.250   0.3420   0.01310   0.00868  -0.0569   0.7487   0.8860
   0.500   0.3636   0.01303   0.00856  -0.0560   0.7465   0.8918
   0.750   0.3957   0.01298   0.00846  -0.0567   0.7446   0.8933
   1.000   0.4232   0.01297   0.00846  -0.0567   0.7416   0.8952
   1.250   0.4490   0.01292   0.00843  -0.0564   0.7379   0.8977
   1.500   0.4743   0.01281   0.00830  -0.0561   0.7347   0.9003
   1.750   0.4988   0.01264   0.00811  -0.0557   0.7318   0.9029
   2.000   0.5248   0.01253   0.00794  -0.0558   0.7293   0.9053
   2.250   0.5469   0.01237   0.00782  -0.0548   0.7252   0.9067
   2.500   0.5722   0.01221   0.00767  -0.0545   0.7210   0.9078
   2.750   0.6003   0.01201   0.00747  -0.0547   0.7174   0.9087
   3.000   0.6308   0.01183   0.00725  -0.0554   0.7144   0.9095
   3.250   0.6527   0.01171   0.00718  -0.0544   0.7094   0.9108
   3.500   0.6771   0.01153   0.00703  -0.0540   0.7045   0.9118
   3.750   0.7057   0.01133   0.00681  -0.0544   0.7005   0.9128
   4.000   0.7285   0.01119   0.00671  -0.0537   0.6950   0.9139
   4.250   0.7529   0.01101   0.00656  -0.0533   0.6889   0.9147
   4.500   0.7800   0.01082   0.00637  -0.0534   0.6834   0.9156
   4.750   0.8015   0.01068   0.00629  -0.0525   0.6746   0.9167
   5.000   0.8261   0.01052   0.00616  -0.0522   0.6659   0.9173
   5.250   0.8510   0.01038   0.00603  -0.0520   0.6557   0.9179
   5.500   0.8740   0.01030   0.00598  -0.0514   0.6428   0.9185
   5.750   0.8971   0.01026   0.00592  -0.0508   0.6279   0.9194
   6.000   0.9185   0.01026   0.00589  -0.0499   0.6101   0.9200
   6.250   0.9363   0.01030   0.00589  -0.0482   0.5901   0.9206
   6.500   0.9519   0.01044   0.00594  -0.0462   0.5695   0.9214
   6.750   0.9646   0.01061   0.00605  -0.0436   0.5476   0.9222
   7.000   0.9741   0.01081   0.00619  -0.0405   0.5266   0.9232
   7.250   0.9822   0.01113   0.00645  -0.0371   0.5041   0.9248
   7.500   0.9889   0.01161   0.00683  -0.0338   0.4786   0.9261
   7.750   0.9938   0.01221   0.00732  -0.0305   0.4487   0.9274
   8.000   0.9974   0.01296   0.00793  -0.0271   0.4172   0.9287
   8.250   1.0019   0.01379   0.00864  -0.0242   0.3856   0.9300
   8.500   1.0075   0.01469   0.00942  -0.0216   0.3552   0.9313
   8.750   1.0170   0.01552   0.01015  -0.0197   0.3302   0.9323
   9.000   1.0260   0.01641   0.01095  -0.0178   0.3047   0.9332
   9.250   1.0329   0.01737   0.01179  -0.0156   0.2775   0.9346
   9.500   1.0392   0.01836   0.01267  -0.0134   0.2505   0.9360
   9.750   1.0482   0.01929   0.01351  -0.0117   0.2261   0.9371
  10.000   1.0555   0.02036   0.01446  -0.0098   0.1986   0.9384
  10.250   1.0630   0.02146   0.01543  -0.0080   0.1723   0.9396
  10.500   1.0708   0.02259   0.01644  -0.0064   0.1482   0.9409
  10.750   1.0779   0.02380   0.01752  -0.0048   0.1233   0.9423
  11.000   1.0862   0.02498   0.01860  -0.0033   0.1012   0.9436
  11.250   1.0941   0.02623   0.01975  -0.0019   0.0812   0.9449
  11.500   1.0973   0.02784   0.02120  -0.0002   0.0551   0.9463
  11.750   1.0981   0.02967   0.02287   0.0017   0.0320   0.9477
  12.000   1.1003   0.03145   0.02457   0.0034   0.0203   0.9495
  12.250   1.1098   0.03273   0.02591   0.0045   0.0179   0.9512
  12.500   1.1159   0.03433   0.02755   0.0057   0.0158   0.9532
  12.750   1.1255   0.03570   0.02902   0.0066   0.0149   0.9554
  13.000   1.1343   0.03715   0.03055   0.0074   0.0140   0.9581
  13.250   1.1410   0.03891   0.03239   0.0081   0.0133   0.9610
  13.500   1.1476   0.04083   0.03439   0.0086   0.0128   0.9643
  13.750   1.1490   0.04342   0.03709   0.0091   0.0123   0.9682
  14.000   1.1579   0.04546   0.03923   0.0088   0.0121   0.9723
  14.250   1.1657   0.04775   0.04164   0.0084   0.0118   0.9803
  14.500   1.1699   0.05000   0.04399   0.0086   0.0116   1.0000
  14.750   1.1734   0.05255   0.04664   0.0086   0.0112   1.0000
  15.000   1.1766   0.05519   0.04937   0.0086   0.0111   1.0000
  15.250   1.1798   0.05790   0.05218   0.0084   0.0110   1.0000
  15.500   1.1821   0.06078   0.05514   0.0081   0.0107   1.0000
  15.750   1.1845   0.06370   0.05815   0.0077   0.0106   1.0000
  16.000   1.1868   0.06666   0.06120   0.0072   0.0104   1.0000
  16.250   1.1878   0.06984   0.06447   0.0067   0.0102   1.0000
  16.500   1.1890   0.07303   0.06774   0.0061   0.0100   1.0000
  16.750   1.1907   0.07620   0.07099   0.0055   0.0100   1.0000
  17.000   1.1928   0.07934   0.07422   0.0047   0.0099   1.0000
  17.250   1.1939   0.08258   0.07754   0.0041   0.0097   1.0000
  17.500   1.1958   0.08573   0.08078   0.0034   0.0096   1.0000
  17.750   1.1974   0.08875   0.08391   0.0033   0.0094   1.0000
  18.000   1.1979   0.09226   0.08756   0.0025   0.0094   1.0000
  18.250   1.1972   0.09615   0.09158   0.0009   0.0093   1.0000
  18.500   1.1937   0.10071   0.09630  -0.0013   0.0092   1.0000
  18.750   1.1915   0.10495   0.10068  -0.0031   0.0091   1.0000
  19.000   1.1879   0.10948   0.10537  -0.0051   0.0090   1.0000
  19.250   1.1839   0.11409   0.11012  -0.0072   0.0091   1.0000
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