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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e521-il-1000000.txt
Download as CSV file: xf-e521-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.0606   0.09934   0.09639  -0.0096   1.0000   0.0030
 -17.500  -1.0799   0.09144   0.08837  -0.0140   1.0000   0.0030
 -17.250  -1.1024   0.08324   0.08001  -0.0185   1.0000   0.0030
 -17.000  -1.1178   0.07653   0.07317  -0.0221   1.0000   0.0030
 -16.750  -1.1315   0.07038   0.06688  -0.0253   1.0000   0.0030
 -16.500  -1.1472   0.06414   0.06050  -0.0285   1.0000   0.0030
 -16.250  -1.1588   0.05887   0.05509  -0.0308   1.0000   0.0030
 -16.000  -1.1672   0.05435   0.05045  -0.0327   1.0000   0.0030
 -15.750  -1.1727   0.05045   0.04644  -0.0340   1.0000   0.0031
 -15.500  -1.1801   0.04660   0.04247  -0.0349   1.0000   0.0031
 -15.250  -1.1848   0.04332   0.03907  -0.0354   1.0000   0.0031
 -15.000  -1.1895   0.04026   0.03590  -0.0355   1.0000   0.0032
 -14.750  -1.1900   0.03779   0.03333  -0.0352   1.0000   0.0031
 -14.500  -1.1901   0.03547   0.03090  -0.0348   1.0000   0.0032
 -14.250  -1.1889   0.03338   0.02872  -0.0341   1.0000   0.0033
 -14.000  -1.1870   0.03141   0.02664  -0.0332   1.0000   0.0033
 -13.750  -1.1836   0.02967   0.02481  -0.0321   1.0000   0.0033
 -13.500  -1.1776   0.02817   0.02322  -0.0310   1.0000   0.0035
 -13.250  -1.1699   0.02683   0.02181  -0.0299   1.0000   0.0037
 -13.000  -1.1639   0.02542   0.02032  -0.0286   1.0000   0.0037
 -12.750  -1.1545   0.02430   0.01912  -0.0274   1.0000   0.0038
 -12.500  -1.1509   0.02280   0.01752  -0.0255   1.0000   0.0040
 -12.250  -1.1454   0.02146   0.01609  -0.0237   1.0000   0.0043
 -12.000  -1.1353   0.02046   0.01504  -0.0221   1.0000   0.0046
 -11.750  -1.1133   0.01962   0.01415  -0.0227   0.9567   0.0054
 -11.500  -1.0967   0.01896   0.01328  -0.0218   0.9052   0.0056
 -11.250  -1.0899   0.01818   0.01235  -0.0191   0.8865   0.0066
 -11.000  -1.0788   0.01758   0.01169  -0.0168   0.8757   0.0077
 -10.500  -1.0548   0.01649   0.01048  -0.0123   0.8612   0.0103
 -10.250  -1.0379   0.01610   0.01003  -0.0108   0.8560   0.0116
 -10.000  -1.0203   0.01560   0.00948  -0.0094   0.8515   0.0135
  -9.750  -1.0010   0.01514   0.00902  -0.0084   0.8473   0.0153
  -9.500  -0.9796   0.01480   0.00863  -0.0076   0.8435   0.0166
  -9.250  -0.9602   0.01431   0.00810  -0.0065   0.8400   0.0196
  -9.000  -0.9384   0.01393   0.00771  -0.0057   0.8369   0.0219
  -8.750  -0.9162   0.01354   0.00730  -0.0050   0.8337   0.0251
  -8.500  -0.8942   0.01313   0.00690  -0.0043   0.8306   0.0294
  -8.250  -0.8719   0.01273   0.00651  -0.0037   0.8277   0.0358
  -8.000  -0.8488   0.01239   0.00617  -0.0031   0.8250   0.0424
  -7.750  -0.8259   0.01198   0.00581  -0.0025   0.8224   0.0535
  -7.500  -0.8024   0.01159   0.00547  -0.0020   0.8198   0.0646
  -7.250  -0.7793   0.01117   0.00514  -0.0015   0.8172   0.0807
  -7.000  -0.7554   0.01080   0.00484  -0.0011   0.8147   0.0963
  -6.750  -0.7310   0.01047   0.00456  -0.0007   0.8122   0.1115
  -6.500  -0.7063   0.01019   0.00431  -0.0004   0.8097   0.1281
  -6.250  -0.6814   0.00985   0.00405  -0.0001   0.8076   0.1477
  -6.000  -0.6561   0.00953   0.00382   0.0001   0.8052   0.1679
  -5.750  -0.6307   0.00923   0.00360   0.0003   0.8027   0.1891
  -5.500  -0.6056   0.00890   0.00338   0.0006   0.8002   0.2169
  -5.250  -0.5800   0.00861   0.00317   0.0008   0.7980   0.2440
  -5.000  -0.5545   0.00833   0.00299   0.0010   0.7954   0.2732
  -4.750  -0.5287   0.00802   0.00280   0.0011   0.7932   0.3047
  -4.500  -0.5025   0.00773   0.00263   0.0012   0.7905   0.3355
  -4.250  -0.4764   0.00744   0.00246   0.0014   0.7877   0.3694
  -4.000  -0.4499   0.00719   0.00231   0.0015   0.7849   0.4023
  -3.750  -0.4236   0.00694   0.00216   0.0016   0.7822   0.4366
  -3.500  -0.3968   0.00671   0.00204   0.0016   0.7793   0.4695
  -3.250  -0.3699   0.00646   0.00191   0.0017   0.7763   0.5062
  -3.000  -0.3432   0.00620   0.00180   0.0017   0.7730   0.5439
  -2.750  -0.3160   0.00601   0.00170   0.0018   0.7698   0.5783
  -2.500  -0.2885   0.00589   0.00164   0.0018   0.7667   0.6079
  -2.250  -0.2604   0.00577   0.00161   0.0017   0.7634   0.6321
  -2.000  -0.2318   0.00570   0.00157   0.0016   0.7597   0.6510
  -1.750  -0.2032   0.00565   0.00154   0.0014   0.7560   0.6663
  -1.500  -0.1744   0.00564   0.00152   0.0013   0.7525   0.6792
  -1.250  -0.1455   0.00562   0.00153   0.0011   0.7488   0.6897
  -1.000  -0.1164   0.00559   0.00152   0.0009   0.7445   0.6983
  -0.750  -0.0873   0.00559   0.00150   0.0006   0.7403   0.7065
  -0.500  -0.0584   0.00559   0.00150   0.0005   0.7358   0.7130
  -0.250  -0.0291   0.00558   0.00150   0.0002   0.7305   0.7195
   0.000   0.0000   0.00558   0.00148   0.0000   0.7251   0.7251
   0.250   0.0291   0.00558   0.00150  -0.0002   0.7196   0.7305
   0.500   0.0584   0.00559   0.00150  -0.0005   0.7129   0.7358
   0.750   0.0873   0.00559   0.00150  -0.0007   0.7066   0.7403
   1.000   0.1164   0.00559   0.00152  -0.0009   0.6983   0.7445
   1.250   0.1455   0.00562   0.00153  -0.0011   0.6897   0.7488
   1.500   0.1744   0.00564   0.00152  -0.0013   0.6792   0.7525
   1.750   0.2032   0.00565   0.00154  -0.0014   0.6663   0.7560
   2.250   0.2604   0.00577   0.00161  -0.0017   0.6322   0.7634
   2.500   0.2885   0.00589   0.00164  -0.0018   0.6080   0.7667
   2.750   0.3160   0.00601   0.00170  -0.0018   0.5782   0.7698
   3.000   0.3432   0.00620   0.00180  -0.0017   0.5439   0.7730
   3.250   0.3700   0.00645   0.00191  -0.0017   0.5064   0.7762
   3.500   0.3968   0.00671   0.00204  -0.0016   0.4695   0.7793
   3.750   0.4236   0.00693   0.00216  -0.0016   0.4367   0.7822
   4.000   0.4499   0.00719   0.00231  -0.0015   0.4023   0.7849
   4.250   0.4764   0.00744   0.00246  -0.0014   0.3696   0.7877
   4.500   0.5025   0.00772   0.00263  -0.0013   0.3359   0.7905
   4.750   0.5287   0.00802   0.00280  -0.0011   0.3048   0.7932
   5.000   0.5545   0.00833   0.00299  -0.0010   0.2731   0.7954
   5.250   0.5799   0.00861   0.00317  -0.0008   0.2438   0.7980
   5.500   0.6054   0.00890   0.00338  -0.0006   0.2165   0.8003
   5.750   0.6306   0.00923   0.00360  -0.0003   0.1892   0.8027
   6.000   0.6561   0.00953   0.00382  -0.0001   0.1680   0.8052
   6.250   0.6813   0.00984   0.00405   0.0001   0.1477   0.8076
   6.500   0.7062   0.01019   0.00431   0.0004   0.1283   0.8097
   6.750   0.7309   0.01047   0.00456   0.0007   0.1115   0.8122
   7.000   0.7553   0.01079   0.00484   0.0011   0.0964   0.8147
   7.250   0.7792   0.01116   0.00514   0.0015   0.0810   0.8172
   7.500   0.8025   0.01157   0.00546   0.0020   0.0662   0.8198
   7.750   0.8256   0.01199   0.00581   0.0026   0.0527   0.8224
   8.000   0.8485   0.01239   0.00617   0.0031   0.0424   0.8250
   8.250   0.8716   0.01273   0.00651   0.0037   0.0355   0.8278
   8.500   0.8939   0.01313   0.00690   0.0044   0.0293   0.8306
   8.750   0.9159   0.01354   0.00730   0.0051   0.0249   0.8338
   9.000   0.9382   0.01393   0.00771   0.0058   0.0219   0.8369
   9.250   0.9599   0.01431   0.00810   0.0065   0.0195   0.8400
   9.500   0.9793   0.01480   0.00863   0.0076   0.0166   0.8435
   9.750   1.0007   0.01513   0.00901   0.0084   0.0153   0.8474
  10.000   1.0200   0.01559   0.00948   0.0095   0.0136   0.8516
  10.250   1.0374   0.01610   0.01004   0.0109   0.0117   0.8561
  10.500   1.0542   0.01648   0.01048   0.0125   0.0104   0.8613
  11.000   1.0785   0.01757   0.01168   0.0169   0.0077   0.8760
  11.250   1.0894   0.01818   0.01235   0.0191   0.0064   0.8869
  11.500   1.0982   0.01886   0.01317   0.0216   0.0062   0.9053
  11.750   1.1138   0.01960   0.01414   0.0226   0.0053   0.9579
  12.000   1.1349   0.02045   0.01505   0.0222   0.0048   1.0000
  12.250   1.1459   0.02138   0.01602   0.0236   0.0045   1.0000
  12.500   1.1558   0.02241   0.01711   0.0251   0.0043   1.0000
  12.750   1.1563   0.02414   0.01895   0.0273   0.0037   1.0000
  13.000   1.1642   0.02536   0.02025   0.0286   0.0037   1.0000
  13.250   1.1721   0.02664   0.02161   0.0298   0.0035   1.0000
  13.500   1.1783   0.02808   0.02313   0.0311   0.0034   1.0000
  13.750   1.1829   0.02968   0.02483   0.0322   0.0034   1.0000
  14.000   1.1865   0.03142   0.02666   0.0332   0.0034   1.0000
  14.250   1.1903   0.03322   0.02855   0.0340   0.0033   1.0000
  14.500   1.1907   0.03539   0.03083   0.0348   0.0032   1.0000
  14.750   1.1909   0.03768   0.03321   0.0352   0.0031   1.0000
  15.000   1.1897   0.04022   0.03586   0.0355   0.0031   1.0000
  15.250   1.1840   0.04339   0.03915   0.0354   0.0031   1.0000
  15.500   1.1824   0.04631   0.04217   0.0350   0.0031   1.0000
  15.750   1.1773   0.04985   0.04582   0.0341   0.0030   1.0000
  16.000   1.1695   0.05401   0.05010   0.0328   0.0030   1.0000
  16.250   1.1581   0.05894   0.05518   0.0308   0.0031   1.0000
  16.500   1.1492   0.06382   0.06018   0.0286   0.0030   1.0000
  16.750   1.1349   0.06984   0.06633   0.0256   0.0030   1.0000
  17.000   1.1203   0.07612   0.07275   0.0223   0.0030   1.0000
  17.250   1.1036   0.08306   0.07983   0.0185   0.0030   1.0000
  17.500   1.0843   0.09068   0.08758   0.0144   0.0030   1.0000
  17.750   1.0618   0.09912   0.09617   0.0097   0.0031   1.0000
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