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E62 (5.62%) (e62-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E62 (5.62%) (e62-il)
Reynolds number: 200,000
Max Cl/Cd: 104.15 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e62-il-200000-n5.txt
Download as CSV file: xf-e62-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3467   0.12259   0.11905  -0.0269   1.0000   0.0113
  -8.750  -0.3461   0.12021   0.11671  -0.0264   1.0000   0.0114
  -8.500  -0.3458   0.11790   0.11444  -0.0258   1.0000   0.0114
  -8.250  -0.3409   0.11507   0.11164  -0.0265   0.9993   0.0114
  -8.000  -0.3266   0.11133   0.10790  -0.0300   0.9968   0.0114
  -7.750  -0.3118   0.10764   0.10421  -0.0337   0.9943   0.0114
  -7.500  -0.2993   0.10418   0.10077  -0.0366   0.9908   0.0114
  -7.250  -0.2911   0.09879   0.09542  -0.0396   0.9871   0.0118
  -7.000  -0.2778   0.09426   0.09090  -0.0418   0.9846   0.0122
  -6.750  -0.2640   0.09069   0.08733  -0.0439   0.9813   0.0126
  -6.500  -0.2514   0.08741   0.08407  -0.0465   0.9757   0.0129
  -6.250  -0.2312   0.08359   0.08025  -0.0511   0.9720   0.0134
  -6.000  -0.2154   0.08011   0.07678  -0.0546   0.9660   0.0140
  -5.750  -0.1947   0.07641   0.07307  -0.0596   0.9610   0.0148
  -5.500  -0.1692   0.07269   0.06935  -0.0658   0.9569   0.0182
  -5.250  -0.1226   0.06874   0.06534  -0.0807   0.9487   0.0213
  -5.000  -0.0863   0.06392   0.06046  -0.0892   0.9461   0.0214
  -4.500  -0.0263   0.05343   0.04982  -0.1026   0.9355   0.0219
  -4.250   0.0082   0.04825   0.04456  -0.1095   0.9334   0.0226
  -4.000   0.0434   0.04370   0.03988  -0.1156   0.9270   0.0226
  -3.750   0.0745   0.04047   0.03656  -0.1192   0.9239   0.0179
  -3.500   0.1336   0.03349   0.02925  -0.1304   0.9226   0.0143
  -3.250   0.1953   0.02640   0.02154  -0.1395   0.9221   0.0118
  -3.000   0.2397   0.02348   0.01817  -0.1439   0.9209   0.0114
  -2.750   0.2865   0.01980   0.01383  -0.1489   0.9203   0.0113
  -2.500   0.3198   0.01782   0.01136  -0.1503   0.9150   0.0114
  -2.250   0.3593   0.01537   0.00840  -0.1529   0.9132   0.0124
  -2.000   0.3946   0.01446   0.00731  -0.1545   0.9106   0.0165
  -1.750   0.4310   0.01363   0.00633  -0.1561   0.9086   0.0206
  -1.500   0.4660   0.01280   0.00540  -0.1576   0.9052   0.0263
  -1.250   0.4975   0.01234   0.00491  -0.1584   0.8998   0.0472
  -1.000   0.5337   0.01177   0.00455  -0.1603   0.8967   0.1235
  -0.750   0.5714   0.01126   0.00435  -0.1626   0.8943   0.2407
  -0.500   0.6008   0.01094   0.00431  -0.1631   0.8872   0.3544
  -0.250   0.6366   0.01033   0.00424  -0.1650   0.8833   0.5640
   0.000   0.6567   0.00948   0.00406  -0.1626   0.8763   1.0000
   0.250   0.6915   0.00941   0.00384  -0.1639   0.8700   1.0000
   0.500   0.7244   0.00937   0.00370  -0.1648   0.8618   1.0000
   0.750   0.7609   0.00929   0.00352  -0.1665   0.8546   1.0000
   1.000   0.7920   0.00930   0.00346  -0.1671   0.8444   1.0000
   1.250   0.8240   0.00931   0.00342  -0.1678   0.8339   1.0000
   1.500   0.8559   0.00933   0.00338  -0.1685   0.8227   1.0000
   1.750   0.8869   0.00937   0.00337  -0.1690   0.8108   1.0000
   2.000   0.9166   0.00945   0.00340  -0.1693   0.7974   1.0000
   2.250   0.9452   0.00954   0.00345  -0.1693   0.7826   1.0000
   2.500   0.9731   0.00966   0.00359  -0.1692   0.7672   1.0000
   2.750   1.0005   0.00980   0.00370  -0.1689   0.7508   1.0000
   3.000   1.0274   0.00996   0.00382  -0.1686   0.7325   1.0000
   3.250   1.0528   0.01014   0.00398  -0.1679   0.7115   1.0000
   3.500   1.0779   0.01035   0.00415  -0.1672   0.6883   1.0000
   3.750   1.1021   0.01060   0.00441  -0.1663   0.6609   1.0000
   4.000   1.1251   0.01090   0.00463  -0.1651   0.6271   1.0000
   4.250   1.1463   0.01129   0.00489  -0.1636   0.5841   1.0000
   4.500   1.1653   0.01182   0.00521  -0.1617   0.5303   1.0000
   4.750   1.1818   0.01253   0.00563  -0.1594   0.4657   1.0000
   5.000   1.1965   0.01343   0.00619  -0.1569   0.3959   1.0000
   5.250   1.2117   0.01437   0.00681  -0.1547   0.3287   1.0000
   5.500   1.2278   0.01531   0.00755  -0.1527   0.2684   1.0000
   5.750   1.2441   0.01630   0.00828  -0.1508   0.2103   1.0000
   6.000   1.2607   0.01732   0.00906  -0.1491   0.1578   1.0000
   6.250   1.2757   0.01854   0.00994  -0.1471   0.1019   1.0000
   6.500   1.2912   0.01972   0.01088  -0.1452   0.0608   1.0000
   6.750   1.3076   0.02084   0.01189  -0.1434   0.0351   1.0000
   7.000   1.3223   0.02217   0.01314  -0.1412   0.0189   1.0000
   7.250   1.3384   0.02335   0.01448  -0.1391   0.0137   1.0000
   7.500   1.3513   0.02483   0.01605  -0.1366   0.0098   1.0000
   7.750   1.3655   0.02604   0.01745  -0.1342   0.0084   1.0000
   8.000   1.3772   0.02749   0.01918  -0.1315   0.0076   1.0000
   8.250   1.3881   0.02910   0.02096  -0.1287   0.0069   1.0000
   8.500   1.3989   0.03087   0.02290  -0.1260   0.0064   1.0000
   8.750   1.4101   0.03281   0.02504  -0.1235   0.0061   1.0000
   9.000   1.4217   0.03503   0.02746  -0.1211   0.0058   1.0000
   9.250   1.4337   0.03758   0.03027  -0.1189   0.0056   1.0000
   9.500   1.4446   0.04054   0.03353  -0.1166   0.0054   1.0000
   9.750   1.4526   0.04379   0.03712  -0.1140   0.0053   1.0000
  10.000   1.4536   0.04764   0.04137  -0.1108   0.0051   1.0000
  10.250   1.4457   0.05225   0.04642  -0.1070   0.0049   1.0000
  10.500   1.4362   0.05594   0.05048  -0.1033   0.0047   1.0000
  10.750   1.4347   0.05808   0.05291  -0.1006   0.0043   1.0000
  11.000   1.4249   0.06187   0.05701  -0.0979   0.0042   1.0000
  11.250   1.4148   0.06568   0.06113  -0.0958   0.0040   1.0000
  11.500   1.4041   0.06971   0.06543  -0.0944   0.0037   1.0000
  11.750   1.3867   0.07507   0.07108  -0.0937   0.0037   1.0000
  12.000   1.3684   0.08089   0.07716  -0.0940   0.0038   1.0000
  12.250   1.3505   0.08710   0.08362  -0.0953   0.0036   1.0000
  12.500   1.3309   0.09422   0.09096  -0.0980   0.0037   1.0000
  12.750   1.3102   0.10231   0.09926  -0.1019   0.0037   1.0000
  13.000   1.2898   0.11143   0.10856  -0.1074   0.0039   1.0000
  13.250   1.2650   0.12287   0.12013  -0.1149   0.0044   1.0000
  13.500   1.2477   0.13402   0.13142  -0.1226   0.0045   1.0000
  13.750   1.0581   0.14455   0.14245  -0.1177   0.0061   1.0000
  14.000   1.0269   0.15936   0.15732  -0.1259   0.0064   1.0000
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