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E591 (e591-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E591 (e591-il)
Reynolds number: 100,000
Max Cl/Cd: 57.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e591-il-100000-n5.txt
Download as CSV file: xf-e591-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E591                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0720   0.09532   0.09039  -0.0790   0.9388   0.0369
  -8.250  -0.0661   0.09104   0.08613  -0.0820   0.9299   0.0373
  -8.000  -0.0564   0.08613   0.08122  -0.0863   0.9235   0.0369
  -7.750  -0.0548   0.08156   0.07668  -0.0891   0.9128   0.0365
  -7.500  -0.0532   0.07463   0.06975  -0.0951   0.9064   0.0357
  -7.250  -0.1163   0.05844   0.05346  -0.1063   0.8849   0.0338
  -7.000  -0.1139   0.04288   0.03710  -0.1334   0.8724   0.0334
  -6.750  -0.0951   0.03784   0.03147  -0.1400   0.8602   0.0336
  -6.500  -0.0534   0.03326   0.02617  -0.1477   0.8559   0.0344
  -6.250  -0.0256   0.03153   0.02429  -0.1492   0.8469   0.0352
  -6.000   0.0118   0.02971   0.02225  -0.1523   0.8406   0.0367
  -5.750   0.0576   0.02757   0.01968  -0.1568   0.8366   0.0392
  -5.500   0.0848   0.02658   0.01866  -0.1573   0.8261   0.0410
  -5.250   0.1269   0.02509   0.01693  -0.1603   0.8202   0.0431
  -5.000   0.1630   0.02397   0.01572  -0.1621   0.8121   0.0452
  -4.750   0.1993   0.02307   0.01470  -0.1639   0.8032   0.0488
  -4.500   0.2408   0.02214   0.01373  -0.1667   0.7961   0.0533
  -4.250   0.2730   0.02144   0.01297  -0.1678   0.7851   0.0577
  -4.000   0.3155   0.02063   0.01207  -0.1708   0.7772   0.0656
  -3.750   0.3483   0.02002   0.01141  -0.1720   0.7658   0.0749
  -3.500   0.3897   0.01922   0.01059  -0.1750   0.7566   0.0931
  -3.250   0.4256   0.01848   0.00999  -0.1771   0.7453   0.1330
  -3.000   0.4626   0.01798   0.00967  -0.1791   0.7350   0.2043
  -2.750   0.4961   0.01785   0.00953  -0.1802   0.7238   0.2554
  -2.500   0.5271   0.01788   0.00951  -0.1807   0.7125   0.2958
  -2.250   0.5603   0.01794   0.00952  -0.1814   0.7021   0.3282
  -2.000   0.5881   0.01803   0.00954  -0.1812   0.6901   0.3503
  -1.750   0.6199   0.01807   0.00944  -0.1816   0.6801   0.3705
  -1.500   0.6469   0.01814   0.00944  -0.1813   0.6684   0.3869
  -1.250   0.6769   0.01818   0.00933  -0.1814   0.6580   0.4023
  -1.000   0.7045   0.01823   0.00932  -0.1812   0.6470   0.4153
  -0.750   0.7327   0.01829   0.00929  -0.1810   0.6367   0.4281
  -0.500   0.7613   0.01837   0.00923  -0.1810   0.6263   0.4423
  -0.250   0.7880   0.01845   0.00930  -0.1806   0.6160   0.4544
   0.000   0.8163   0.01855   0.00929  -0.1805   0.6063   0.4682
   0.250   0.8430   0.01868   0.00936  -0.1801   0.5962   0.4824
   0.500   0.8704   0.01879   0.00941  -0.1798   0.5868   0.4963
   0.750   0.8966   0.01894   0.00953  -0.1794   0.5772   0.5111
   1.000   0.9239   0.01909   0.00960  -0.1791   0.5680   0.5274
   1.250   0.9498   0.01925   0.00975  -0.1786   0.5588   0.5436
   1.500   0.9757   0.01942   0.00989  -0.1781   0.5499   0.5605
   1.750   1.0017   0.01961   0.01005  -0.1776   0.5415   0.5788
   2.000   1.0265   0.01980   0.01025  -0.1769   0.5325   0.5983
   2.250   1.0528   0.02000   0.01039  -0.1765   0.5248   0.6196
   2.500   1.0762   0.02022   0.01066  -0.1756   0.5159   0.6426
   2.750   1.1018   0.02042   0.01081  -0.1750   0.5085   0.6680
   3.000   1.1238   0.02064   0.01112  -0.1738   0.5001   0.6950
   3.250   1.1464   0.02084   0.01134  -0.1726   0.4925   0.7270
   3.500   1.1678   0.02103   0.01155  -0.1712   0.4855   0.7642
   3.750   1.1845   0.02116   0.01181  -0.1689   0.4777   0.8116
   4.000   1.1960   0.02109   0.01181  -0.1653   0.4716   0.9271
   4.250   1.2217   0.02144   0.01210  -0.1651   0.4639   1.0000
   4.500   1.2468   0.02184   0.01243  -0.1648   0.4563   1.0000
   4.750   1.2731   0.02224   0.01270  -0.1647   0.4498   1.0000
   5.000   1.2955   0.02268   0.01316  -0.1639   0.4420   1.0000
   5.250   1.3198   0.02310   0.01348  -0.1634   0.4353   1.0000
   5.500   1.3429   0.02355   0.01389  -0.1627   0.4285   1.0000
   5.750   1.3644   0.02402   0.01437  -0.1618   0.4212   1.0000
   6.000   1.3881   0.02446   0.01471  -0.1612   0.4152   1.0000
   6.250   1.4081   0.02498   0.01526  -0.1600   0.4083   1.0000
   6.500   1.4278   0.02547   0.01577  -0.1588   0.4015   1.0000
   6.750   1.4509   0.02594   0.01613  -0.1581   0.3960   1.0000
   7.000   1.4666   0.02653   0.01680  -0.1563   0.3891   1.0000
   7.250   1.4844   0.02707   0.01735  -0.1548   0.3827   1.0000
   7.500   1.5057   0.02759   0.01779  -0.1539   0.3773   1.0000
   7.750   1.5196   0.02827   0.01859  -0.1519   0.3707   1.0000
   8.000   1.5359   0.02890   0.01923  -0.1502   0.3647   1.0000
   8.250   1.5555   0.02947   0.01973  -0.1491   0.3595   1.0000
   8.500   1.5673   0.03028   0.02068  -0.1470   0.3531   1.0000
   8.750   1.5816   0.03101   0.02144  -0.1452   0.3473   1.0000
   9.000   1.6003   0.03163   0.02199  -0.1440   0.3424   1.0000
   9.250   1.6094   0.03261   0.02314  -0.1417   0.3362   1.0000
   9.500   1.6215   0.03349   0.02408  -0.1398   0.3306   1.0000
   9.750   1.6380   0.03423   0.02476  -0.1385   0.3258   1.0000
  10.000   1.6461   0.03537   0.02605  -0.1363   0.3202   1.0000
  10.250   1.6553   0.03648   0.02725  -0.1343   0.3146   1.0000
  10.500   1.6689   0.03740   0.02816  -0.1328   0.3099   1.0000
  10.750   1.6775   0.03865   0.02950  -0.1310   0.3048   1.0000
  11.000   1.6834   0.04008   0.03106  -0.1289   0.2993   1.0000
  11.250   1.6931   0.04130   0.03232  -0.1273   0.2945   1.0000
  11.500   1.7043   0.04250   0.03354  -0.1260   0.2900   1.0000
  11.750   1.7055   0.04442   0.03564  -0.1239   0.2848   1.0000
  12.000   1.7110   0.04606   0.03737  -0.1223   0.2799   1.0000
  12.250   1.7235   0.04723   0.03852  -0.1212   0.2756   1.0000
  12.500   1.7222   0.04957   0.04104  -0.1195   0.2708   1.0000
  12.750   1.7225   0.05185   0.04347  -0.1181   0.2659   1.0000
  13.000   1.7289   0.05362   0.04528  -0.1169   0.2615   1.0000
  13.250   1.7355   0.05546   0.04717  -0.1159   0.2573   1.0000
  13.500   1.7277   0.05877   0.05070  -0.1147   0.2525   1.0000
  13.750   1.7276   0.06140   0.05344  -0.1138   0.2480   1.0000
  14.000   1.7377   0.06297   0.05500  -0.1132   0.2441   1.0000
  14.250   1.7297   0.06668   0.05890  -0.1125   0.2396   1.0000
  14.500   1.7198   0.07075   0.06317  -0.1122   0.2349   1.0000
  14.750   1.7216   0.07346   0.06596  -0.1118   0.2308   1.0000
  15.000   1.7333   0.07495   0.06743  -0.1114   0.2272   1.0000
  15.250   1.7072   0.08156   0.07434  -0.1120   0.2224   1.0000
  15.500   1.6971   0.08618   0.07911  -0.1125   0.2179   1.0000
  15.750   1.7058   0.08812   0.08107  -0.1124   0.2143   1.0000
  16.000   1.6957   0.09294   0.08603  -0.1132   0.2103   1.0000
  16.250   1.6609   0.10180   0.09517  -0.1157   0.2052   1.0000
  16.500   1.6610   0.10520   0.09864  -0.1164   0.2013   1.0000
  16.750   1.6859   0.10453   0.09792  -0.1155   0.1983   1.0000
  17.000   1.5893   0.12480   0.11865  -0.1241   0.1906   1.0000
  17.250   1.5953   0.12733   0.12123  -0.1248   0.1871   1.0000
  17.500   1.6268   0.12519   0.11907  -0.1232   0.1850   1.0000
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