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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 100,000
Max Cl/Cd: 34.71 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e521-il-100000-n5.txt
Download as CSV file: xf-e521-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.7603   0.12473   0.11976  -0.0025   1.0000   0.0222
 -15.250  -0.7900   0.11242   0.10735  -0.0098   1.0000   0.0216
 -15.000  -0.8193   0.10114   0.09590  -0.0168   1.0000   0.0213
 -14.750  -0.8417   0.09221   0.08680  -0.0225   1.0000   0.0210
 -14.500  -0.8617   0.08442   0.07881  -0.0272   1.0000   0.0210
 -14.250  -0.8796   0.07761   0.07178  -0.0310   1.0000   0.0210
 -14.000  -0.8951   0.07171   0.06564  -0.0339   1.0000   0.0213
 -13.750  -0.9074   0.06661   0.06031  -0.0360   1.0000   0.0215
 -13.500  -0.9168   0.06216   0.05562  -0.0373   1.0000   0.0219
 -13.250  -0.9242   0.05820   0.05138  -0.0382   1.0000   0.0225
 -13.000  -0.9299   0.05465   0.04770  -0.0386   1.0000   0.0235
 -12.750  -0.9315   0.05183   0.04480  -0.0388   1.0000   0.0244
 -12.500  -0.9321   0.04926   0.04213  -0.0387   1.0000   0.0255
 -12.250  -0.9314   0.04681   0.03954  -0.0384   1.0000   0.0270
 -12.000  -0.9285   0.04441   0.03693  -0.0377   1.0000   0.0287
 -11.750  -0.9226   0.04224   0.03449  -0.0369   1.0000   0.0305
 -11.500  -0.9192   0.04003   0.03226  -0.0361   1.0000   0.0324
 -11.250  -0.9138   0.03825   0.03042  -0.0352   1.0000   0.0346
 -11.000  -0.9060   0.03658   0.02861  -0.0342   1.0000   0.0375
 -10.750  -0.8955   0.03501   0.02684  -0.0331   1.0000   0.0406
 -10.500  -0.8901   0.03332   0.02519  -0.0319   1.0000   0.0440
 -10.250  -0.8804   0.03194   0.02368  -0.0306   1.0000   0.0480
 -10.000  -0.8700   0.03057   0.02219  -0.0293   1.0000   0.0524
  -9.750  -0.8620   0.02927   0.02091  -0.0278   1.0000   0.0575
  -9.500  -0.8506   0.02816   0.01970  -0.0263   1.0000   0.0640
  -9.250  -0.8431   0.02700   0.01858  -0.0243   1.0000   0.0705
  -9.000  -0.8334   0.02605   0.01761  -0.0224   1.0000   0.0787
  -8.750  -0.8229   0.02521   0.01672  -0.0205   1.0000   0.0890
  -8.500  -0.8166   0.02441   0.01600  -0.0179   1.0000   0.0989
  -8.250  -0.8163   0.02385   0.01548  -0.0141   0.9995   0.1085
  -8.000  -0.7907   0.02294   0.01452  -0.0151   0.9865   0.1277
  -7.750  -0.7646   0.02205   0.01369  -0.0161   0.9774   0.1501
  -7.500  -0.7375   0.02125   0.01292  -0.0172   0.9697   0.1749
  -7.250  -0.7119   0.02052   0.01223  -0.0179   0.9621   0.2020
  -7.000  -0.6856   0.01982   0.01160  -0.0186   0.9558   0.2318
  -6.750  -0.6616   0.01921   0.01103  -0.0187   0.9491   0.2620
  -6.500  -0.6372   0.01863   0.01054  -0.0189   0.9430   0.2948
  -6.250  -0.6128   0.01812   0.01009  -0.0189   0.9374   0.3292
  -6.000  -0.5912   0.01767   0.00974  -0.0182   0.9311   0.3638
  -5.750  -0.5668   0.01725   0.00941  -0.0180   0.9263   0.4013
  -5.500  -0.5456   0.01691   0.00917  -0.0171   0.9205   0.4380
  -5.250  -0.5228   0.01664   0.00900  -0.0163   0.9153   0.4759
  -5.000  -0.4974   0.01646   0.00893  -0.0158   0.9113   0.5136
  -4.750  -0.4748   0.01641   0.00896  -0.0147   0.9059   0.5481
  -4.500  -0.4493   0.01645   0.00905  -0.0140   0.9013   0.5799
  -4.250  -0.4220   0.01657   0.00916  -0.0135   0.8975   0.6079
  -4.000  -0.3966   0.01677   0.00935  -0.0127   0.8929   0.6304
  -3.750  -0.3724   0.01693   0.00945  -0.0119   0.8878   0.6515
  -3.500  -0.3452   0.01714   0.00959  -0.0114   0.8839   0.6687
  -3.250  -0.3200   0.01734   0.00973  -0.0106   0.8794   0.6841
  -3.000  -0.2964   0.01754   0.00986  -0.0097   0.8740   0.6983
  -2.750  -0.2707   0.01771   0.00994  -0.0090   0.8697   0.7113
  -2.500  -0.2467   0.01786   0.01002  -0.0082   0.8649   0.7238
  -2.250  -0.2227   0.01806   0.01018  -0.0072   0.8593   0.7344
  -2.000  -0.1956   0.01823   0.01031  -0.0067   0.8549   0.7436
  -1.750  -0.1725   0.01834   0.01036  -0.0057   0.8494   0.7539
  -1.500  -0.1481   0.01847   0.01046  -0.0049   0.8436   0.7627
  -1.250  -0.1211   0.01855   0.01050  -0.0043   0.8393   0.7705
  -1.000  -0.1006   0.01860   0.01051  -0.0031   0.8322   0.7804
  -0.750  -0.0728   0.01871   0.01062  -0.0026   0.8269   0.7861
  -0.500  -0.0508   0.01870   0.01057  -0.0015   0.8207   0.7953
  -0.250  -0.0243   0.01879   0.01067  -0.0009   0.8141   0.8006
   0.000   0.0000   0.01872   0.01057   0.0000   0.8087   0.8088
   0.500   0.0508   0.01870   0.01057   0.0015   0.7953   0.8207
   0.750   0.0728   0.01871   0.01061   0.0025   0.7861   0.8269
   1.000   0.1007   0.01860   0.01051   0.0031   0.7804   0.8322
   1.250   0.1211   0.01855   0.01050   0.0043   0.7705   0.8393
   1.500   0.1481   0.01847   0.01046   0.0049   0.7627   0.8436
   1.750   0.1726   0.01834   0.01036   0.0057   0.7539   0.8494
   2.000   0.1957   0.01823   0.01031   0.0067   0.7436   0.8549
   2.250   0.2227   0.01806   0.01018   0.0072   0.7344   0.8593
   2.500   0.2468   0.01786   0.01003   0.0082   0.7238   0.8649
   2.750   0.2707   0.01771   0.00994   0.0090   0.7113   0.8697
   3.000   0.2964   0.01754   0.00986   0.0097   0.6982   0.8740
   3.250   0.3201   0.01735   0.00973   0.0106   0.6842   0.8794
   3.500   0.3452   0.01714   0.00959   0.0114   0.6687   0.8839
   3.750   0.3724   0.01693   0.00945   0.0119   0.6515   0.8878
   4.000   0.3966   0.01677   0.00936   0.0127   0.6304   0.8929
   4.250   0.4219   0.01657   0.00916   0.0135   0.6079   0.8975
   4.500   0.4492   0.01646   0.00905   0.0140   0.5799   0.9013
   4.750   0.4748   0.01641   0.00897   0.0147   0.5483   0.9059
   5.000   0.4973   0.01646   0.00893   0.0158   0.5136   0.9113
   5.250   0.5228   0.01664   0.00900   0.0163   0.4759   0.9153
   5.500   0.5455   0.01691   0.00917   0.0171   0.4379   0.9205
   5.750   0.5668   0.01725   0.00941   0.0180   0.4014   0.9263
   6.000   0.5911   0.01767   0.00974   0.0183   0.3636   0.9311
   6.250   0.6128   0.01812   0.01009   0.0189   0.3294   0.9374
   6.500   0.6373   0.01863   0.01053   0.0189   0.2952   0.9429
   6.750   0.6616   0.01921   0.01103   0.0187   0.2620   0.9491
   7.000   0.6855   0.01982   0.01160   0.0186   0.2317   0.9557
   7.250   0.7119   0.02052   0.01223   0.0179   0.2022   0.9621
   7.500   0.7375   0.02125   0.01292   0.0172   0.1751   0.9697
   7.750   0.7645   0.02205   0.01368   0.0162   0.1499   0.9774
   8.000   0.7906   0.02294   0.01452   0.0151   0.1278   0.9865
   8.250   0.8162   0.02385   0.01548   0.0141   0.1087   0.9994
   8.500   0.8166   0.02441   0.01600   0.0179   0.0988   1.0000
   8.750   0.8228   0.02521   0.01672   0.0205   0.0889   1.0000
   9.000   0.8333   0.02604   0.01759   0.0224   0.0786   1.0000
   9.250   0.8429   0.02700   0.01857   0.0244   0.0704   1.0000
   9.500   0.8505   0.02815   0.01969   0.0263   0.0640   1.0000
   9.750   0.8619   0.02925   0.02089   0.0278   0.0576   1.0000
  10.000   0.8701   0.03054   0.02217   0.0293   0.0524   1.0000
  10.250   0.8803   0.03193   0.02367   0.0307   0.0481   1.0000
  10.500   0.8899   0.03331   0.02517   0.0319   0.0439   1.0000
  10.750   0.8955   0.03500   0.02684   0.0331   0.0407   1.0000
  11.000   0.9059   0.03656   0.02860   0.0342   0.0375   1.0000
  11.250   0.9138   0.03824   0.03041   0.0352   0.0346   1.0000
  11.500   0.9190   0.04001   0.03223   0.0361   0.0323   1.0000
  11.750   0.9225   0.04219   0.03446   0.0369   0.0303   1.0000
  12.000   0.9284   0.04439   0.03692   0.0378   0.0286   1.0000
  12.250   0.9318   0.04679   0.03952   0.0384   0.0271   1.0000
  12.500   0.9327   0.04920   0.04207   0.0387   0.0256   1.0000
  12.750   0.9320   0.05179   0.04476   0.0388   0.0244   1.0000
  13.000   0.9302   0.05464   0.04768   0.0387   0.0235   1.0000
  13.250   0.9248   0.05817   0.05134   0.0383   0.0226   1.0000
  13.500   0.9176   0.06210   0.05555   0.0374   0.0219   1.0000
  13.750   0.9072   0.06669   0.06040   0.0359   0.0214   1.0000
  14.000   0.8949   0.07178   0.06572   0.0338   0.0211   1.0000
  14.250   0.8805   0.07751   0.07168   0.0310   0.0210   1.0000
  14.500   0.8621   0.08444   0.07882   0.0271   0.0209   1.0000
  14.750   0.8421   0.09222   0.08681   0.0224   0.0210   1.0000
  15.000   0.8192   0.10130   0.09607   0.0166   0.0213   1.0000
  15.250   0.7888   0.11289   0.10783   0.0094   0.0216   1.0000
  15.500   0.7612   0.12468   0.11971   0.0024   0.0221   1.0000
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