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EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 520 AIRFOIL (e520-il)
Reynolds number: 50,000
Max Cl/Cd: 27.81 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e520-il-50000-n5.txt
Download as CSV file: xf-e520-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 520 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7438   0.10878   0.10191  -0.0153   1.0000   0.0606
 -14.000  -0.7892   0.09498   0.08796  -0.0237   1.0000   0.0585
 -13.750  -0.8210   0.08567   0.07842  -0.0290   1.0000   0.0578
 -13.500  -0.8419   0.07900   0.07154  -0.0323   1.0000   0.0581
 -13.250  -0.8577   0.07359   0.06591  -0.0344   1.0000   0.0593
 -13.000  -0.8705   0.06877   0.06084  -0.0359   1.0000   0.0607
 -12.750  -0.8818   0.06430   0.05606  -0.0368   1.0000   0.0627
 -12.500  -0.8900   0.06024   0.05159  -0.0372   1.0000   0.0648
 -12.250  -0.8786   0.05804   0.04950  -0.0369   1.0000   0.0682
 -12.000  -0.8760   0.05534   0.04667  -0.0367   1.0000   0.0723
 -11.750  -0.8743   0.05239   0.04329  -0.0364   1.0000   0.0771
 -11.500  -0.8642   0.05042   0.04144  -0.0360   1.0000   0.0824
 -11.250  -0.8552   0.04813   0.03888  -0.0354   1.0000   0.0891
 -11.000  -0.8463   0.04623   0.03704  -0.0349   1.0000   0.0962
 -10.750  -0.8355   0.04427   0.03492  -0.0342   1.0000   0.1052
 -10.500  -0.8267   0.04248   0.03310  -0.0335   1.0000   0.1152
 -10.250  -0.8173   0.04077   0.03142  -0.0327   1.0000   0.1262
 -10.000  -0.8072   0.03913   0.02978  -0.0319   1.0000   0.1385
  -9.750  -0.7983   0.03755   0.02822  -0.0310   1.0000   0.1527
  -9.500  -0.7890   0.03606   0.02671  -0.0299   1.0000   0.1682
  -9.250  -0.7806   0.03464   0.02531  -0.0288   1.0000   0.1859
  -9.000  -0.7723   0.03333   0.02408  -0.0274   1.0000   0.2042
  -8.750  -0.7654   0.03214   0.02300  -0.0257   1.0000   0.2234
  -8.500  -0.7593   0.03107   0.02199  -0.0237   1.0000   0.2447
  -8.250  -0.7540   0.03012   0.02118  -0.0214   1.0000   0.2663
  -8.000  -0.7507   0.02930   0.02044  -0.0187   1.0000   0.2890
  -7.750  -0.7522   0.02868   0.01995  -0.0149   1.0000   0.3092
  -7.500  -0.7584   0.02821   0.01957  -0.0103   1.0000   0.3285
  -7.250  -0.7644   0.02774   0.01911  -0.0056   1.0000   0.3494
  -7.000  -0.7566   0.02722   0.01869  -0.0031   0.9955   0.3782
  -6.750  -0.7319   0.02681   0.01839  -0.0032   0.9862   0.4151
  -6.500  -0.7050   0.02661   0.01822  -0.0034   0.9783   0.4525
  -6.250  -0.6746   0.02680   0.01845  -0.0035   0.9715   0.4860
  -6.000  -0.6419   0.02720   0.01877  -0.0039   0.9656   0.5164
  -5.750  -0.6123   0.02757   0.01902  -0.0038   0.9590   0.5432
  -5.500  -0.5754   0.02820   0.01950  -0.0047   0.9543   0.5660
  -5.250  -0.5491   0.02851   0.01964  -0.0043   0.9474   0.5869
  -5.000  -0.5142   0.02911   0.02005  -0.0049   0.9425   0.6041
  -4.750  -0.4792   0.02959   0.02035  -0.0057   0.9380   0.6206
  -4.500  -0.4535   0.02993   0.02054  -0.0051   0.9314   0.6357
  -4.250  -0.4216   0.03023   0.02066  -0.0057   0.9264   0.6504
  -4.000  -0.3947   0.03045   0.02074  -0.0055   0.9208   0.6642
  -3.750  -0.3694   0.03060   0.02076  -0.0051   0.9146   0.6775
  -3.250  -0.3227   0.03071   0.02061  -0.0040   0.9027   0.7037
  -3.000  -0.2894   0.03092   0.02072  -0.0047   0.8979   0.7135
  -2.750  -0.2600   0.03100   0.02071  -0.0050   0.8929   0.7237
  -2.500  -0.2429   0.03097   0.02059  -0.0035   0.8857   0.7351
  -2.250  -0.2144   0.03094   0.02046  -0.0039   0.8808   0.7459
  -2.000  -0.1898   0.03107   0.02054  -0.0033   0.8741   0.7539
  -1.750  -0.1677   0.03098   0.02038  -0.0027   0.8680   0.7642
  -1.500  -0.1418   0.03103   0.02037  -0.0025   0.8618   0.7727
  -1.250  -0.1184   0.03102   0.02033  -0.0020   0.8551   0.7812
  -1.000  -0.0982   0.03092   0.02016  -0.0012   0.8488   0.7912
  -0.750  -0.0704   0.03102   0.02026  -0.0013   0.8417   0.7975
  -0.500  -0.0465   0.03089   0.02009  -0.0010   0.8360   0.8068
  -0.250  -0.0234   0.03101   0.02022  -0.0004   0.8278   0.8130
   0.000   0.0000   0.03089   0.02007   0.0000   0.8217   0.8217
   0.250   0.0234   0.03101   0.02022   0.0004   0.8131   0.8278
   0.500   0.0466   0.03089   0.02009   0.0010   0.8068   0.8360
   0.750   0.0705   0.03101   0.02025   0.0013   0.7975   0.8417
   1.000   0.0986   0.03091   0.02015   0.0011   0.7913   0.8488
   1.250   0.1186   0.03102   0.02033   0.0020   0.7811   0.8551
   1.500   0.1418   0.03103   0.02037   0.0025   0.7727   0.8619
   1.750   0.1677   0.03098   0.02038   0.0027   0.7643   0.8680
   2.000   0.1899   0.03107   0.02054   0.0033   0.7539   0.8742
   2.250   0.2151   0.03093   0.02045   0.0038   0.7462   0.8808
   2.500   0.2426   0.03098   0.02060   0.0035   0.7353   0.8858
   2.750   0.2598   0.03101   0.02070   0.0050   0.7238   0.8930
   3.000   0.2896   0.03091   0.02072   0.0047   0.7138   0.8980
   3.250   0.3226   0.03070   0.02061   0.0040   0.7037   0.9028
   3.500   0.3391   0.03067   0.02068   0.0057   0.6907   0.9101
   3.750   0.3696   0.03057   0.02074   0.0051   0.6775   0.9146
   4.000   0.3947   0.03043   0.02072   0.0055   0.6641   0.9209
   4.250   0.4217   0.03021   0.02065   0.0057   0.6504   0.9265
   4.500   0.4536   0.02992   0.02053   0.0051   0.6358   0.9315
   4.750   0.4791   0.02959   0.02035   0.0057   0.6207   0.9381
   5.000   0.5142   0.02911   0.02005   0.0049   0.6042   0.9426
   5.250   0.5490   0.02851   0.01964   0.0043   0.5869   0.9476
   5.500   0.5757   0.02819   0.01949   0.0046   0.5660   0.9544
   5.750   0.6125   0.02755   0.01900   0.0038   0.5431   0.9591
   6.000   0.6419   0.02719   0.01876   0.0038   0.5164   0.9657
   6.250   0.6748   0.02679   0.01843   0.0035   0.4860   0.9716
   6.500   0.7051   0.02660   0.01821   0.0034   0.4522   0.9785
   6.750   0.7321   0.02680   0.01838   0.0032   0.4148   0.9864
   7.000   0.7567   0.02721   0.01868   0.0031   0.3777   0.9957
   7.250   0.7642   0.02773   0.01909   0.0056   0.3495   1.0000
   7.500   0.7583   0.02820   0.01956   0.0103   0.3285   1.0000
   7.750   0.7521   0.02867   0.01994   0.0150   0.3091   1.0000
   8.000   0.7508   0.02929   0.02043   0.0187   0.2888   1.0000
   8.250   0.7543   0.03012   0.02117   0.0214   0.2660   1.0000
   8.500   0.7600   0.03107   0.02198   0.0236   0.2445   1.0000
   8.750   0.7663   0.03215   0.02300   0.0256   0.2232   1.0000
   9.000   0.7733   0.03334   0.02408   0.0272   0.2040   1.0000
   9.250   0.7817   0.03465   0.02533   0.0286   0.1855   1.0000
   9.500   0.7899   0.03606   0.02672   0.0298   0.1679   1.0000
   9.750   0.7994   0.03755   0.02822   0.0308   0.1525   1.0000
  10.000   0.8084   0.03913   0.02979   0.0317   0.1383   1.0000
  10.250   0.8184   0.04078   0.03143   0.0326   0.1259   1.0000
  10.500   0.8275   0.04250   0.03313   0.0333   0.1149   1.0000
  10.750   0.8370   0.04427   0.03491   0.0340   0.1051   1.0000
  11.000   0.8474   0.04624   0.03705   0.0347   0.0960   1.0000
  11.250   0.8568   0.04814   0.03890   0.0352   0.0890   1.0000
  11.500   0.8653   0.05044   0.04145   0.0357   0.0821   1.0000
  11.750   0.8753   0.05244   0.04335   0.0362   0.0769   1.0000
  12.000   0.8766   0.05539   0.04671   0.0365   0.0719   1.0000
  12.250   0.8802   0.05805   0.04952   0.0366   0.0681   1.0000
  12.500   0.8903   0.06037   0.05175   0.0369   0.0646   1.0000
  12.750   0.8825   0.06442   0.05619   0.0365   0.0625   1.0000
  13.000   0.8716   0.06887   0.06095   0.0356   0.0606   1.0000
  13.250   0.8588   0.07366   0.06598   0.0341   0.0591   1.0000
  13.500   0.8432   0.07914   0.07169   0.0320   0.0581   1.0000
  13.750   0.8228   0.08563   0.07838   0.0288   0.0575   1.0000
  14.000   0.7901   0.09517   0.08817   0.0234   0.0585   1.0000
  14.250   0.7448   0.10901   0.10214   0.0149   0.0606   1.0000
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