Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 520 AIRFOIL (e520-il)
Reynolds number: 500,000
Max Cl/Cd: 62.32 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e520-il-500000.txt
Download as CSV file: xf-e520-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -0.9219   0.15887   0.15619   0.0258   1.0000   0.0069
 -19.250  -0.9405   0.14937   0.14655   0.0201   1.0000   0.0069
 -19.000  -0.9574   0.14059   0.13762   0.0148   1.0000   0.0070
 -18.750  -0.9704   0.13305   0.12995   0.0103   1.0000   0.0070
 -18.500  -0.9833   0.12574   0.12251   0.0060   1.0000   0.0070
 -18.250  -0.9952   0.11879   0.11544   0.0020   1.0000   0.0070
 -18.000  -1.0080   0.11181   0.10832  -0.0020   1.0000   0.0070
 -17.750  -1.0183   0.10548   0.10185  -0.0055   1.0000   0.0070
 -17.500  -1.0278   0.09940   0.09565  -0.0089   1.0000   0.0071
 -17.250  -1.0389   0.09328   0.08939  -0.0121   1.0000   0.0071
 -17.000  -1.0471   0.08778   0.08376  -0.0150   1.0000   0.0072
 -16.750  -1.0556   0.08242   0.07827  -0.0176   1.0000   0.0072
 -16.500  -1.0623   0.07737   0.07307  -0.0201   1.0000   0.0075
 -16.250  -1.0715   0.07229   0.06787  -0.0223   1.0000   0.0075
 -16.000  -1.0873   0.06652   0.06198  -0.0246   1.0000   0.0079
 -15.750  -1.0933   0.06223   0.05756  -0.0262   1.0000   0.0079
 -15.500  -1.0976   0.05834   0.05357  -0.0276   1.0000   0.0080
 -15.250  -1.1024   0.05456   0.04967  -0.0287   1.0000   0.0080
 -15.000  -1.1006   0.05168   0.04674  -0.0296   1.0000   0.0086
 -14.750  -1.1029   0.04849   0.04345  -0.0301   1.0000   0.0087
 -14.500  -1.1026   0.04575   0.04062  -0.0305   1.0000   0.0090
 -14.250  -1.1025   0.04313   0.03790  -0.0305   1.0000   0.0093
 -14.000  -1.0962   0.04119   0.03586  -0.0305   1.0000   0.0100
 -13.750  -1.0915   0.03916   0.03372  -0.0303   1.0000   0.0103
 -13.500  -1.0971   0.03630   0.03077  -0.0297   1.0000   0.0107
 -13.250  -1.0987   0.03391   0.02833  -0.0290   1.0000   0.0115
 -13.000  -1.0917   0.03231   0.02667  -0.0284   1.0000   0.0121
 -12.750  -1.0849   0.03073   0.02503  -0.0277   1.0000   0.0129
 -12.500  -1.0744   0.02946   0.02366  -0.0270   1.0000   0.0138
 -12.250  -1.0744   0.02742   0.02156  -0.0257   1.0000   0.0151
 -12.000  -1.0657   0.02609   0.02021  -0.0248   1.0000   0.0164
 -11.750  -1.0525   0.02511   0.01919  -0.0241   1.0000   0.0179
 -11.500  -1.0411   0.02399   0.01803  -0.0233   1.0000   0.0196
 -11.250  -1.0327   0.02268   0.01673  -0.0223   1.0000   0.0215
 -11.000  -1.0058   0.02178   0.01575  -0.0241   0.9368   0.0240
 -10.750  -0.9924   0.02090   0.01467  -0.0232   0.8925   0.0263
 -10.500  -0.9850   0.02004   0.01373  -0.0211   0.8741   0.0291
 -10.250  -0.9729   0.01942   0.01298  -0.0193   0.8628   0.0316
 -10.000  -0.9636   0.01865   0.01211  -0.0172   0.8539   0.0348
  -9.750  -0.9541   0.01792   0.01137  -0.0150   0.8468   0.0392
  -9.500  -0.9415   0.01740   0.01078  -0.0129   0.8404   0.0434
  -9.250  -0.9308   0.01679   0.01016  -0.0106   0.8350   0.0502
  -9.000  -0.9149   0.01619   0.00957  -0.0091   0.8299   0.0586
  -8.750  -0.8975   0.01565   0.00904  -0.0078   0.8255   0.0688
  -8.500  -0.8793   0.01515   0.00855  -0.0066   0.8217   0.0805
  -8.250  -0.8599   0.01463   0.00806  -0.0057   0.8178   0.0943
  -8.000  -0.8399   0.01412   0.00761  -0.0048   0.8138   0.1097
  -7.750  -0.8192   0.01365   0.00720  -0.0039   0.8103   0.1273
  -7.250  -0.7761   0.01277   0.00644  -0.0025   0.8042   0.1675
  -7.000  -0.7537   0.01233   0.00608  -0.0020   0.8007   0.1911
  -6.750  -0.7311   0.01189   0.00573  -0.0015   0.7975   0.2179
  -6.500  -0.7087   0.01144   0.00540  -0.0009   0.7947   0.2485
  -6.250  -0.6858   0.01105   0.00510  -0.0003   0.7920   0.2793
  -6.000  -0.6621   0.01063   0.00482   0.0000   0.7891   0.3119
  -5.750  -0.6381   0.01023   0.00454   0.0004   0.7861   0.3469
  -5.500  -0.6137   0.00987   0.00429   0.0007   0.7832   0.3815
  -5.250  -0.5890   0.00954   0.00407   0.0010   0.7804   0.4153
  -5.000  -0.5641   0.00925   0.00387   0.0013   0.7779   0.4501
  -4.750  -0.5385   0.00899   0.00371   0.0016   0.7753   0.4840
  -4.500  -0.5122   0.00876   0.00359   0.0017   0.7723   0.5149
  -4.250  -0.4855   0.00859   0.00351   0.0018   0.7693   0.5436
  -4.000  -0.4583   0.00849   0.00344   0.0019   0.7665   0.5685
  -3.750  -0.4307   0.00845   0.00341   0.0019   0.7638   0.5883
  -3.500  -0.4027   0.00845   0.00341   0.0019   0.7610   0.6050
  -3.250  -0.3742   0.00844   0.00342   0.0018   0.7576   0.6193
  -3.000  -0.3456   0.00845   0.00341   0.0016   0.7543   0.6316
  -2.750  -0.3171   0.00849   0.00341   0.0015   0.7512   0.6426
  -2.500  -0.2885   0.00854   0.00345   0.0015   0.7485   0.6513
  -2.250  -0.2597   0.00860   0.00346   0.0013   0.7454   0.6599
  -2.000  -0.2308   0.00863   0.00352   0.0011   0.7417   0.6670
  -1.750  -0.2020   0.00867   0.00351   0.0010   0.7381   0.6743
  -1.500  -0.1732   0.00871   0.00355   0.0009   0.7349   0.6800
  -1.250  -0.1444   0.00879   0.00357   0.0008   0.7317   0.6868
  -1.000  -0.1155   0.00879   0.00361   0.0006   0.7275   0.6916
  -0.750  -0.0866   0.00882   0.00364   0.0004   0.7235   0.6969
  -0.500  -0.0577   0.00885   0.00360   0.0003   0.7199   0.7025
  -0.250  -0.0289   0.00886   0.00364   0.0002   0.7162   0.7065
   0.000   0.0000   0.00886   0.00368   0.0000   0.7113   0.7111
   0.250   0.0290   0.00887   0.00365  -0.0002   0.7068   0.7161
   0.500   0.0577   0.00886   0.00361  -0.0003   0.7026   0.7199
   0.750   0.0866   0.00881   0.00363  -0.0004   0.6966   0.7235
   1.000   0.1155   0.00879   0.00360  -0.0006   0.6913   0.7276
   1.250   0.1445   0.00879   0.00357  -0.0008   0.6865   0.7318
   1.500   0.1733   0.00871   0.00355  -0.0009   0.6800   0.7349
   1.750   0.2020   0.00867   0.00352  -0.0010   0.6743   0.7382
   2.000   0.2309   0.00863   0.00352  -0.0012   0.6670   0.7417
   2.250   0.2598   0.00860   0.00346  -0.0013   0.6599   0.7454
   2.500   0.2886   0.00854   0.00344  -0.0015   0.6512   0.7485
   2.750   0.3171   0.00849   0.00341  -0.0016   0.6427   0.7513
   3.000   0.3457   0.00845   0.00341  -0.0017   0.6317   0.7543
   3.250   0.3743   0.00844   0.00342  -0.0018   0.6194   0.7577
   3.500   0.4028   0.00845   0.00341  -0.0019   0.6050   0.7610
   3.750   0.4308   0.00845   0.00341  -0.0020   0.5884   0.7638
   4.000   0.4584   0.00849   0.00345  -0.0019   0.5686   0.7665
   4.250   0.4856   0.00859   0.00351  -0.0018   0.5436   0.7693
   4.500   0.5123   0.00876   0.00359  -0.0017   0.5150   0.7724
   4.750   0.5385   0.00899   0.00371  -0.0016   0.4838   0.7753
   5.000   0.5642   0.00925   0.00387  -0.0014   0.4501   0.7779
   5.250   0.5891   0.00954   0.00407  -0.0011   0.4149   0.7804
   5.500   0.6139   0.00987   0.00429  -0.0007   0.3815   0.7832
   5.750   0.6382   0.01024   0.00454  -0.0004   0.3467   0.7861
   6.000   0.6622   0.01064   0.00482  -0.0001   0.3113   0.7891
   6.250   0.6859   0.01105   0.00510   0.0003   0.2789   0.7921
   6.500   0.7089   0.01145   0.00541   0.0008   0.2481   0.7947
   6.750   0.7314   0.01190   0.00574   0.0014   0.2179   0.7975
   7.000   0.7541   0.01232   0.00607   0.0019   0.1913   0.8007
   7.250   0.7765   0.01277   0.00644   0.0025   0.1673   0.8041
   7.750   0.8197   0.01366   0.00720   0.0039   0.1273   0.8103
   8.000   0.8404   0.01412   0.00762   0.0047   0.1098   0.8138
   8.250   0.8604   0.01463   0.00806   0.0056   0.0941   0.8178
   8.500   0.8799   0.01516   0.00855   0.0065   0.0804   0.8217
   8.750   0.8981   0.01566   0.00904   0.0077   0.0686   0.8255
   9.000   0.9156   0.01619   0.00957   0.0090   0.0585   0.8298
   9.250   0.9316   0.01679   0.01016   0.0104   0.0501   0.8349
   9.500   0.9425   0.01741   0.01079   0.0127   0.0432   0.8403
   9.750   0.9553   0.01792   0.01137   0.0148   0.0389   0.8467
  10.000   0.9648   0.01864   0.01210   0.0170   0.0345   0.8537
  10.250   0.9743   0.01940   0.01296   0.0191   0.0316   0.8627
  10.500   0.9862   0.02004   0.01372   0.0209   0.0289   0.8740
  10.750   0.9934   0.02091   0.01467   0.0230   0.0263   0.8923
  11.000   1.0066   0.02179   0.01576   0.0240   0.0240   0.9361
  11.250   1.0340   0.02269   0.01673   0.0220   0.0214   1.0000
  11.500   1.0410   0.02410   0.01813   0.0232   0.0192   1.0000
  11.750   1.0535   0.02514   0.01923   0.0240   0.0177   1.0000
  12.000   1.0655   0.02622   0.02035   0.0247   0.0164   1.0000
  12.250   1.0741   0.02756   0.02171   0.0256   0.0151   1.0000
  12.500   1.0748   0.02954   0.02375   0.0268   0.0139   1.0000
  12.750   1.0860   0.03076   0.02506   0.0275   0.0129   1.0000
  13.000   1.0945   0.03221   0.02657   0.0281   0.0121   1.0000
  13.250   1.0992   0.03401   0.02844   0.0288   0.0115   1.0000
  13.500   1.1023   0.03600   0.03047   0.0293   0.0108   1.0000
  13.750   1.0931   0.03918   0.03374   0.0300   0.0103   1.0000
  14.000   1.1004   0.04097   0.03563   0.0302   0.0098   1.0000
  14.250   1.1023   0.04332   0.03809   0.0303   0.0094   1.0000
  14.500   1.1027   0.04593   0.04081   0.0302   0.0092   1.0000
  14.750   1.1041   0.04856   0.04353   0.0299   0.0088   1.0000
  15.000   1.1065   0.05124   0.04626   0.0292   0.0082   1.0000
  15.250   1.1039   0.05460   0.04973   0.0284   0.0081   1.0000
  15.500   1.0998   0.05829   0.05352   0.0274   0.0081   1.0000
  15.750   1.0916   0.06270   0.05802   0.0258   0.0077   1.0000
  16.000   1.0797   0.06779   0.06323   0.0239   0.0076   1.0000
  16.250   1.0760   0.07193   0.06749   0.0221   0.0076   1.0000
  16.500   1.0618   0.07769   0.07339   0.0198   0.0074   1.0000
  16.750   1.0570   0.08249   0.07834   0.0173   0.0072   1.0000
  17.000   1.0481   0.08782   0.08379   0.0147   0.0073   1.0000
  17.250   1.0393   0.09342   0.08952   0.0119   0.0073   1.0000
  17.500   1.0314   0.09918   0.09542   0.0086   0.0071   1.0000
  17.750   1.0199   0.10548   0.10185   0.0053   0.0071   1.0000
  18.000   1.0093   0.11199   0.10850   0.0016   0.0070   1.0000
  18.250   0.9977   0.11861   0.11525  -0.0021   0.0071   1.0000
  18.500   0.9846   0.12585   0.12262  -0.0063   0.0070   1.0000
  18.750   0.9718   0.13329   0.13019  -0.0108   0.0069   1.0000
  19.000   0.9582   0.14107   0.13811  -0.0154   0.0069   1.0000
<< Back to EPPLER 520 AIRFOIL (e520-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 520 AIRFOIL (e520-il)