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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 50,000
Max Cl/Cd: 48 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e62-il-50000.txt
Download as CSV file: xf-e62-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E62  (5.62%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3546   0.10779   0.10146  -0.0216   1.0000   0.1248
  -6.750  -0.3660   0.10749   0.10129  -0.0208   1.0000   0.1271
  -6.500  -0.3756   0.10782   0.10176  -0.0232   1.0000   0.1284
  -6.250  -0.3656   0.10195   0.09592  -0.0187   1.0000   0.1322
  -6.000  -0.3644   0.09954   0.09356  -0.0176   1.0000   0.1370
  -5.750  -0.3676   0.09862   0.09274  -0.0200   1.0000   0.1416
  -5.500  -0.3659   0.09608   0.09029  -0.0213   1.0000   0.1440
  -5.250  -0.3618   0.09247   0.08672  -0.0176   1.0000   0.1499
  -5.000  -0.3527   0.09183   0.08610  -0.0267   1.0000   0.1569
  -4.750  -0.3525   0.08741   0.08171  -0.0203   1.0000   0.1609
  -4.500  -0.3347   0.08583   0.08013  -0.0294   1.0000   0.1714
  -4.250  -0.3363   0.08187   0.07624  -0.0226   1.0000   0.1759
  -4.000  -0.3208   0.07909   0.07347  -0.0272   1.0000   0.1873
  -3.750  -0.3049   0.07626   0.07063  -0.0304   1.0000   0.2009
  -3.500  -0.2922   0.07324   0.06763  -0.0312   1.0000   0.2155
  -3.250  -0.2816   0.07024   0.06466  -0.0305   1.0000   0.2317
  -3.000  -0.2580   0.06743   0.06181  -0.0350   1.0000   0.2574
  -2.750  -0.2393   0.06479   0.05915  -0.0366   1.0000   0.2839
  -2.500  -0.2296   0.06166   0.05609  -0.0345   1.0000   0.3031
  -2.250  -0.2132   0.05896   0.05337  -0.0345   1.0000   0.3351
  -1.250   0.1256   0.03767   0.02913  -0.1018   1.0000   0.1277
  -1.000   0.1666   0.03524   0.02629  -0.1053   1.0000   0.1226
  -0.750   0.2074   0.03334   0.02383  -0.1083   1.0000   0.1211
  -0.500   0.2448   0.03185   0.02182  -0.1102   1.0000   0.1197
  -0.250   0.2784   0.03082   0.02036  -0.1114   1.0000   0.1235
   0.000   0.3090   0.03006   0.01929  -0.1118   1.0000   0.1347
   0.250   0.3392   0.02945   0.01859  -0.1123   1.0000   0.1748
   0.500   0.3741   0.02617   0.01727  -0.1123   1.0000   1.0000
   0.750   0.3961   0.02690   0.01745  -0.1120   1.0000   1.0000
   1.000   0.4172   0.02768   0.01786  -0.1118   1.0000   1.0000
   1.250   0.4377   0.02850   0.01841  -0.1116   1.0000   1.0000
   1.500   0.4578   0.02937   0.01907  -0.1115   1.0000   1.0000
   1.750   0.4773   0.03030   0.01981  -0.1113   1.0000   1.0000
   2.000   0.4964   0.03128   0.02065  -0.1111   1.0000   1.0000
   2.250   0.5150   0.03232   0.02159  -0.1110   1.0000   1.0000
   2.500   0.5332   0.03343   0.02262  -0.1109   1.0000   1.0000
   2.750   0.5509   0.03460   0.02375  -0.1108   1.0000   1.0000
   3.000   0.5680   0.03585   0.02499  -0.1108   1.0000   1.0000
   3.250   0.6093   0.03759   0.02671  -0.1153   0.9863   1.0000
   3.500   0.6535   0.03912   0.02828  -0.1201   0.9675   1.0000
   3.750   0.6981   0.04044   0.02967  -0.1245   0.9494   1.0000
   4.000   0.7377   0.04154   0.03092  -0.1279   0.9302   1.0000
   4.250   0.7815   0.04248   0.03200  -0.1316   0.9108   1.0000
   4.500   0.8212   0.04328   0.03297  -0.1344   0.8899   1.0000
   4.750   0.8692   0.04376   0.03368  -0.1379   0.8693   1.0000
   5.000   0.9076   0.04416   0.03440  -0.1397   0.8460   1.0000
   5.250   0.9556   0.04403   0.03459  -0.1421   0.8229   1.0000
   5.500   1.0151   0.04291   0.03391  -0.1451   0.7992   1.0000
   5.750   1.0703   0.04119   0.03278  -0.1465   0.7720   1.0000
   6.000   1.1497   0.03680   0.02914  -0.1484   0.7432   1.0000
   6.250   1.2249   0.03163   0.02483  -0.1481   0.6997   1.0000
   6.500   1.2694   0.02781   0.02146  -0.1435   0.6269   1.0000
   6.750   1.2758   0.02658   0.01966  -0.1345   0.4936   1.0000
   7.000   1.2622   0.02880   0.02048  -0.1261   0.3285   1.0000
   7.250   1.2440   0.03301   0.02315  -0.1193   0.1905   1.0000
   7.500   1.2556   0.03782   0.02697  -0.1162   0.1146   1.0000
   7.750   1.3031   0.04174   0.03075  -0.1178   0.0891   1.0000
   8.000   1.3460   0.04573   0.03478  -0.1194   0.0780   1.0000
   8.250   1.3794   0.04986   0.03952  -0.1190   0.0752   1.0000
   8.500   1.4031   0.05430   0.04455  -0.1176   0.0744   1.0000
   8.750   1.4185   0.05895   0.04980  -0.1153   0.0746   1.0000
   9.000   1.4277   0.06378   0.05518  -0.1127   0.0756   1.0000
   9.250   1.4333   0.06884   0.06071  -0.1100   0.0769   1.0000
   9.500   1.4383   0.07433   0.06654  -0.1077   0.0783   1.0000
   9.750   1.4393   0.07937   0.07201  -0.1051   0.0798   1.0000
  10.000   1.4045   0.08313   0.07656  -0.0992   0.0826   1.0000
  10.250   1.3778   0.08763   0.08144  -0.0952   0.0844   1.0000
  10.500   1.3512   0.09221   0.08628  -0.0921   0.0856   1.0000
  10.750   1.3252   0.09728   0.09156  -0.0905   0.0868   1.0000
  11.000   1.2998   0.10295   0.09740  -0.0904   0.0879   1.0000
  11.250   1.2772   0.10931   0.10388  -0.0917   0.0892   1.0000
  11.500   1.2784   0.11578   0.11045  -0.0923   0.0926   1.0000
  11.750   1.2368   0.12410   0.11888  -0.0981   0.0933   1.0000
  12.000   1.1852   0.13947   0.13422  -0.1121   0.0968   1.0000
  12.250   1.1771   0.14877   0.14347  -0.1171   0.1026   1.0000
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