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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 200,000
Max Cl/Cd: 43.22 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e521-il-200000-n5.txt
Download as CSV file: xf-e521-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 521 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8563   0.12893   0.12507   0.0047   1.0000   0.0091
 -16.750  -0.8850   0.11740   0.11326  -0.0017   1.0000   0.0087
 -16.500  -0.9013   0.10922   0.10496  -0.0065   1.0000   0.0088
 -16.250  -0.9176   0.10136   0.09693  -0.0110   1.0000   0.0088
 -16.000  -0.9318   0.09420   0.08961  -0.0150   1.0000   0.0087
 -15.750  -0.9433   0.08770   0.08299  -0.0189   1.0000   0.0089
 -15.500  -0.9551   0.08148   0.07663  -0.0225   1.0000   0.0091
 -15.250  -0.9653   0.07575   0.07075  -0.0256   1.0000   0.0091
 -15.000  -0.9742   0.07048   0.06536  -0.0284   1.0000   0.0095
 -14.750  -0.9835   0.06549   0.06020  -0.0306   1.0000   0.0094
 -14.500  -0.9889   0.06129   0.05586  -0.0325   1.0000   0.0096
 -14.250  -0.9928   0.05753   0.05196  -0.0340   1.0000   0.0100
 -14.000  -0.9974   0.05390   0.04818  -0.0350   1.0000   0.0104
 -13.750  -1.0012   0.05053   0.04466  -0.0356   1.0000   0.0106
 -13.500  -1.0025   0.04761   0.04159  -0.0359   1.0000   0.0111
 -13.250  -1.0032   0.04486   0.03866  -0.0359   1.0000   0.0115
 -13.000  -1.0029   0.04231   0.03596  -0.0356   1.0000   0.0120
 -12.750  -1.0049   0.03971   0.03327  -0.0352   1.0000   0.0124
 -12.500  -1.0031   0.03757   0.03101  -0.0346   1.0000   0.0131
 -12.250  -0.9976   0.03582   0.02917  -0.0340   1.0000   0.0141
 -12.000  -0.9903   0.03424   0.02748  -0.0333   1.0000   0.0154
 -11.750  -0.9820   0.03275   0.02584  -0.0324   1.0000   0.0165
 -11.500  -0.9789   0.03092   0.02397  -0.0312   1.0000   0.0177
 -11.250  -0.9709   0.02952   0.02251  -0.0301   1.0000   0.0190
 -11.000  -0.9604   0.02833   0.02123  -0.0291   1.0000   0.0209
 -10.750  -0.9483   0.02726   0.02003  -0.0280   1.0000   0.0228
 -10.500  -0.9412   0.02587   0.01864  -0.0266   1.0000   0.0251
 -10.250  -0.9290   0.02487   0.01759  -0.0254   1.0000   0.0277
 -10.000  -0.9152   0.02400   0.01659  -0.0243   1.0000   0.0304
  -9.750  -0.9051   0.02295   0.01555  -0.0228   1.0000   0.0338
  -9.500  -0.8854   0.02211   0.01465  -0.0227   0.9668   0.0386
  -9.250  -0.8616   0.02114   0.01363  -0.0234   0.9443   0.0447
  -9.000  -0.8406   0.02046   0.01283  -0.0231   0.9295   0.0512
  -8.750  -0.8240   0.01975   0.01211  -0.0219   0.9177   0.0593
  -8.500  -0.8064   0.01913   0.01146  -0.0207   0.9091   0.0684
  -8.250  -0.7884   0.01857   0.01084  -0.0196   0.9016   0.0788
  -8.000  -0.7702   0.01804   0.01028  -0.0184   0.8955   0.0910
  -7.750  -0.7516   0.01750   0.00976  -0.0173   0.8891   0.1053
  -7.500  -0.7327   0.01698   0.00927  -0.0162   0.8840   0.1218
  -7.250  -0.7129   0.01650   0.00882  -0.0152   0.8795   0.1402
  -7.000  -0.6926   0.01603   0.00838  -0.0143   0.8746   0.1599
  -6.750  -0.6725   0.01558   0.00796  -0.0133   0.8702   0.1816
  -6.500  -0.6521   0.01514   0.00757  -0.0124   0.8666   0.2053
  -6.250  -0.6304   0.01472   0.00721  -0.0117   0.8623   0.2305
  -6.000  -0.6091   0.01431   0.00687  -0.0109   0.8583   0.2578
  -5.750  -0.5877   0.01391   0.00654  -0.0100   0.8548   0.2859
  -5.500  -0.5657   0.01354   0.00623  -0.0093   0.8515   0.3159
  -5.250  -0.5432   0.01316   0.00596  -0.0087   0.8476   0.3473
  -5.000  -0.5208   0.01281   0.00570  -0.0080   0.8439   0.3798
  -4.750  -0.4982   0.01248   0.00547  -0.0072   0.8407   0.4148
  -4.500  -0.4752   0.01217   0.00527  -0.0064   0.8378   0.4503
  -4.250  -0.4515   0.01189   0.00511  -0.0059   0.8339   0.4872
  -4.000  -0.4275   0.01165   0.00501  -0.0052   0.8303   0.5233
  -3.750  -0.4030   0.01148   0.00496  -0.0046   0.8271   0.5579
  -3.500  -0.3778   0.01140   0.00495  -0.0039   0.8243   0.5895
  -3.250  -0.3515   0.01137   0.00499  -0.0036   0.8204   0.6166
  -3.000  -0.3250   0.01139   0.00504  -0.0032   0.8165   0.6392
  -2.750  -0.2983   0.01143   0.00508  -0.0028   0.8130   0.6576
  -2.500  -0.2715   0.01149   0.00509  -0.0024   0.8099   0.6733
  -2.250  -0.2443   0.01155   0.00515  -0.0022   0.8054   0.6865
  -2.000  -0.2172   0.01160   0.00518  -0.0020   0.8010   0.6983
  -1.750  -0.1902   0.01165   0.00516  -0.0017   0.7972   0.7095
  -1.500  -0.1630   0.01171   0.00521  -0.0015   0.7931   0.7189
  -1.250  -0.1358   0.01177   0.00527  -0.0013   0.7878   0.7272
  -1.000  -0.1089   0.01179   0.00523  -0.0010   0.7833   0.7364
  -0.750  -0.0815   0.01184   0.00528  -0.0007   0.7788   0.7425
  -0.500  -0.0545   0.01186   0.00529  -0.0005   0.7728   0.7503
  -0.250  -0.0271   0.01187   0.00529  -0.0002   0.7679   0.7557
   0.000   0.0000   0.01188   0.00531   0.0000   0.7620   0.7620
   0.250   0.0272   0.01187   0.00529   0.0002   0.7557   0.7679
   0.500   0.0545   0.01186   0.00529   0.0005   0.7503   0.7728
   0.750   0.0815   0.01184   0.00528   0.0007   0.7425   0.7788
   1.000   0.1089   0.01179   0.00523   0.0010   0.7364   0.7833
   1.250   0.1358   0.01177   0.00527   0.0013   0.7272   0.7878
   1.500   0.1630   0.01171   0.00521   0.0014   0.7189   0.7931
   1.750   0.1902   0.01164   0.00516   0.0017   0.7095   0.7972
   2.000   0.2172   0.01160   0.00518   0.0020   0.6983   0.8011
   2.250   0.2443   0.01155   0.00515   0.0022   0.6865   0.8054
   2.500   0.2715   0.01149   0.00509   0.0024   0.6732   0.8099
   2.750   0.2983   0.01143   0.00508   0.0028   0.6576   0.8130
   3.000   0.3250   0.01139   0.00504   0.0032   0.6392   0.8165
   3.250   0.3515   0.01137   0.00499   0.0036   0.6166   0.8204
   3.500   0.3778   0.01140   0.00495   0.0039   0.5896   0.8243
   3.750   0.4030   0.01148   0.00496   0.0046   0.5579   0.8271
   4.000   0.4275   0.01165   0.00501   0.0052   0.5234   0.8303
   4.250   0.4515   0.01189   0.00511   0.0059   0.4871   0.8339
   4.500   0.4752   0.01217   0.00527   0.0064   0.4506   0.8378
   4.750   0.4981   0.01248   0.00547   0.0072   0.4150   0.8407
   5.000   0.5207   0.01281   0.00570   0.0080   0.3800   0.8439
   5.250   0.5431   0.01316   0.00596   0.0087   0.3474   0.8476
   5.750   0.5876   0.01391   0.00654   0.0101   0.2858   0.8548
   6.000   0.6089   0.01430   0.00687   0.0109   0.2579   0.8583
   6.250   0.6303   0.01472   0.00721   0.0117   0.2305   0.8624
   6.500   0.6519   0.01514   0.00757   0.0124   0.2054   0.8666
   6.750   0.6723   0.01557   0.00795   0.0134   0.1817   0.8702
   7.000   0.6924   0.01602   0.00838   0.0144   0.1603   0.8746
   7.250   0.7126   0.01650   0.00881   0.0153   0.1404   0.8796
   7.500   0.7325   0.01698   0.00927   0.0162   0.1221   0.8841
   7.750   0.7513   0.01750   0.00976   0.0173   0.1051   0.8892
   8.000   0.7699   0.01804   0.01028   0.0184   0.0907   0.8955
   8.250   0.7881   0.01857   0.01083   0.0196   0.0787   0.9017
   8.500   0.8061   0.01913   0.01145   0.0208   0.0684   0.9093
   8.750   0.8237   0.01974   0.01210   0.0220   0.0593   0.9179
   9.000   0.8403   0.02045   0.01282   0.0231   0.0512   0.9297
   9.250   0.8614   0.02114   0.01362   0.0235   0.0446   0.9446
   9.500   0.8852   0.02211   0.01465   0.0227   0.0386   0.9674
   9.750   0.9048   0.02294   0.01554   0.0228   0.0340   1.0000
  10.000   0.9148   0.02401   0.01659   0.0244   0.0306   1.0000
  10.250   0.9287   0.02487   0.01758   0.0255   0.0277   1.0000
  10.500   0.9408   0.02588   0.01865   0.0266   0.0252   1.0000
  10.750   0.9479   0.02726   0.02003   0.0281   0.0228   1.0000
  11.000   0.9608   0.02828   0.02117   0.0290   0.0208   1.0000
  11.250   0.9711   0.02949   0.02248   0.0301   0.0190   1.0000
  11.500   0.9787   0.03093   0.02397   0.0312   0.0177   1.0000
  11.750   0.9818   0.03276   0.02586   0.0324   0.0165   1.0000
  12.000   0.9903   0.03423   0.02747   0.0333   0.0153   1.0000
  12.250   0.9982   0.03575   0.02910   0.0340   0.0140   1.0000
  12.500   1.0031   0.03757   0.03101   0.0346   0.0132   1.0000
  12.750   1.0053   0.03967   0.03322   0.0352   0.0125   1.0000
  13.000   1.0027   0.04233   0.03598   0.0356   0.0120   1.0000
  13.250   1.0036   0.04482   0.03863   0.0359   0.0115   1.0000
  13.500   1.0028   0.04757   0.04154   0.0359   0.0111   1.0000
  13.750   1.0007   0.05060   0.04474   0.0356   0.0106   1.0000
  14.000   0.9973   0.05392   0.04821   0.0350   0.0103   1.0000
  14.250   0.9937   0.05742   0.05185   0.0340   0.0101   1.0000
  14.500   0.9888   0.06131   0.05589   0.0325   0.0097   1.0000
  14.750   0.9828   0.06560   0.06032   0.0306   0.0095   1.0000
  15.000   0.9759   0.07028   0.06513   0.0283   0.0093   1.0000
  15.250   0.9661   0.07566   0.07064   0.0255   0.0090   1.0000
  15.500   0.9558   0.08136   0.07652   0.0226   0.0092   1.0000
  15.750   0.9459   0.08727   0.08257   0.0191   0.0090   1.0000
  16.000   0.9327   0.09403   0.08946   0.0152   0.0089   1.0000
  16.250   0.9169   0.10151   0.09712   0.0110   0.0089   1.0000
  16.500   0.9009   0.10938   0.10515   0.0065   0.0090   1.0000
  16.750   0.8858   0.11734   0.11323   0.0017   0.0088   1.0000
  17.000   0.8555   0.12929   0.12544  -0.0049   0.0092   1.0000
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