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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 50,000
Max Cl/Cd: 49.48 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e71-il-50000-n5.txt
Download as CSV file: xf-e71-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E71  (5.15%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3772   0.10523   0.09863  -0.0229   1.0000   0.0850
  -7.000  -0.3857   0.10441   0.09793  -0.0231   1.0000   0.0864
  -6.750  -0.3892   0.10324   0.09690  -0.0263   1.0000   0.0871
  -6.500  -0.3797   0.09782   0.09150  -0.0213   1.0000   0.0907
  -6.250  -0.3772   0.09533   0.08906  -0.0208   1.0000   0.0961
  -6.000  -0.3766   0.09387   0.08770  -0.0256   1.0000   0.1000
  -5.750  -0.3726   0.09008   0.08398  -0.0233   1.0000   0.1038
  -5.500  -0.3671   0.08734   0.08129  -0.0231   1.0000   0.1099
  -5.000  -0.3509   0.08112   0.07516  -0.0277   1.0000   0.1180
  -4.750  -0.3400   0.07804   0.07210  -0.0292   1.0000   0.1233
  -4.500  -0.3194   0.07426   0.06831  -0.0365   1.0000   0.1297
  -4.250  -0.3083   0.07099   0.06506  -0.0360   1.0000   0.1332
  -3.750  -0.2093   0.05619   0.04967  -0.0617   1.0000   0.0627
  -3.500  -0.1759   0.05176   0.04506  -0.0666   1.0000   0.0551
  -3.250  -0.0966   0.04357   0.03595  -0.0832   1.0000   0.0468
  -3.000  -0.0562   0.03955   0.03162  -0.0886   1.0000   0.0456
  -2.750  -0.0085   0.03565   0.02720  -0.0950   1.0000   0.0444
  -2.500   0.0394   0.03226   0.02306  -0.1004   1.0000   0.0437
  -2.250   0.0827   0.02962   0.01977  -0.1043   1.0000   0.0436
  -2.000   0.1195   0.02797   0.01742  -0.1063   1.0000   0.0470
  -1.750   0.1513   0.02660   0.01592  -0.1079   1.0000   0.0534
  -1.500   0.1830   0.02543   0.01438  -0.1087   1.0000   0.0568
  -1.250   0.2132   0.02452   0.01309  -0.1090   1.0000   0.0600
  -1.000   0.2436   0.02378   0.01212  -0.1096   1.0000   0.0659
  -0.750   0.2748   0.02324   0.01140  -0.1105   1.0000   0.0779
  -0.500   0.3117   0.02226   0.01087  -0.1128   1.0000   0.1891
  -0.250   0.3210   0.02018   0.01111  -0.1092   1.0000   0.9528
   0.000   0.3459   0.02056   0.01103  -0.1091   1.0000   1.0000
   0.250   0.3702   0.02100   0.01110  -0.1090   1.0000   1.0000
   0.500   0.3952   0.02150   0.01133  -0.1091   0.9990   1.0000
   0.750   0.4327   0.02209   0.01166  -0.1117   0.9909   1.0000
   1.000   0.4711   0.02268   0.01205  -0.1143   0.9831   1.0000
   1.250   0.5071   0.02316   0.01241  -0.1165   0.9736   1.0000
   1.500   0.5437   0.02362   0.01278  -0.1188   0.9640   1.0000
   1.750   0.5811   0.02404   0.01315  -0.1211   0.9544   1.0000
   2.000   0.6198   0.02440   0.01350  -0.1235   0.9446   1.0000
   2.250   0.6552   0.02468   0.01385  -0.1253   0.9328   1.0000
   2.500   0.6913   0.02489   0.01414  -0.1270   0.9204   1.0000
   2.750   0.7280   0.02504   0.01439  -0.1287   0.9073   1.0000
   3.000   0.7656   0.02509   0.01459  -0.1304   0.8936   1.0000
   3.250   0.8045   0.02501   0.01479  -0.1321   0.8791   1.0000
   3.500   0.8378   0.02493   0.01493  -0.1326   0.8611   1.0000
   3.750   0.8758   0.02461   0.01486  -0.1336   0.8429   1.0000
   4.000   0.9148   0.02410   0.01464  -0.1344   0.8232   1.0000
   4.250   0.9532   0.02355   0.01441  -0.1349   0.7994   1.0000
   4.500   0.9872   0.02311   0.01442  -0.1344   0.7681   1.0000
   4.750   1.0225   0.02260   0.01421  -0.1340   0.7273   1.0000
   5.000   1.0589   0.02214   0.01395  -0.1333   0.6678   1.0000
   5.250   1.0934   0.02210   0.01381  -0.1323   0.5750   1.0000
   5.500   1.1161   0.02301   0.01425  -0.1299   0.4626   1.0000
   5.750   1.1298   0.02460   0.01530  -0.1270   0.3549   1.0000
   6.000   1.1409   0.02664   0.01674  -0.1243   0.2489   1.0000
   6.250   1.1516   0.02940   0.01858  -0.1223   0.1319   1.0000
   6.500   1.1671   0.03245   0.02101  -0.1211   0.0553   1.0000
   6.750   1.1851   0.03488   0.02355  -0.1194   0.0399   1.0000
   7.000   1.2022   0.03743   0.02620  -0.1176   0.0345   1.0000
   7.250   1.2242   0.03999   0.02917  -0.1159   0.0315   1.0000
   7.500   1.2488   0.04297   0.03252  -0.1147   0.0292   1.0000
   7.750   1.2731   0.04634   0.03629  -0.1137   0.0277   1.0000
   8.000   1.2932   0.04994   0.04034  -0.1123   0.0264   1.0000
   8.250   1.3072   0.05350   0.04429  -0.1106   0.0250   1.0000
   8.500   1.3155   0.05760   0.04875  -0.1087   0.0236   1.0000
   8.750   1.3188   0.06229   0.05387  -0.1063   0.0228   1.0000
   9.000   1.3194   0.06623   0.05837  -0.1035   0.0223   1.0000
   9.250   1.3145   0.07045   0.06309  -0.1005   0.0219   1.0000
   9.500   1.3045   0.07467   0.06771  -0.0976   0.0217   1.0000
   9.750   1.2895   0.07877   0.07213  -0.0945   0.0217   1.0000
  10.000   1.2722   0.08318   0.07683  -0.0924   0.0217   1.0000
  10.250   1.2538   0.08806   0.08196  -0.0913   0.0218   1.0000
  10.500   1.2352   0.09343   0.08754  -0.0917   0.0220   1.0000
  10.750   1.2163   0.09946   0.09376  -0.0934   0.0222   1.0000
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