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E221 (9.39%) (e221-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E221 (9.39%) (e221-il)
Reynolds number: 100,000
Max Cl/Cd: 48.18 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e221-il-100000-n5.txt
Download as CSV file: xf-e221-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E221  (9.39%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5269   0.11077   0.10585   0.0047   1.0000   0.0308
  -9.750  -0.5332   0.10354   0.09866  -0.0002   1.0000   0.0254
  -9.500  -0.5302   0.09964   0.09480  -0.0013   1.0000   0.0248
  -9.250  -0.5285   0.09556   0.09076  -0.0031   1.0000   0.0242
  -9.000  -0.5288   0.09106   0.08631  -0.0054   1.0000   0.0236
  -8.750  -0.5310   0.08622   0.08153  -0.0082   1.0000   0.0230
  -8.500  -0.5347   0.08112   0.07649  -0.0116   1.0000   0.0225
  -8.250  -0.5434   0.07506   0.07050  -0.0167   1.0000   0.0219
  -8.000  -0.5542   0.06824   0.06366  -0.0213   1.0000   0.0212
  -7.750  -0.5729   0.05721   0.05224  -0.0261   1.0000   0.0195
  -7.500  -0.5719   0.05288   0.04772  -0.0264   1.0000   0.0194
  -7.250  -0.5682   0.04871   0.04327  -0.0262   1.0000   0.0192
  -7.000  -0.5620   0.04465   0.03890  -0.0256   1.0000   0.0191
  -6.750  -0.5534   0.04076   0.03462  -0.0247   1.0000   0.0190
  -6.500  -0.5423   0.03711   0.03054  -0.0234   1.0000   0.0190
  -6.250  -0.5286   0.03388   0.02682  -0.0219   1.0000   0.0192
  -6.000  -0.5128   0.03107   0.02351  -0.0203   1.0000   0.0197
  -5.750  -0.4955   0.02917   0.02147  -0.0193   1.0000   0.0208
  -5.500  -0.4767   0.02759   0.01970  -0.0180   1.0000   0.0221
  -5.250  -0.4578   0.02578   0.01761  -0.0165   1.0000   0.0231
  -5.000  -0.4391   0.02400   0.01552  -0.0148   1.0000   0.0237
  -4.750  -0.4205   0.02251   0.01383  -0.0131   0.9994   0.0245
  -4.500  -0.3828   0.02086   0.01191  -0.0150   0.9846   0.0259
  -4.250  -0.3484   0.01936   0.01038  -0.0166   0.9679   0.0283
  -4.000  -0.3131   0.01846   0.00935  -0.0182   0.9507   0.0339
  -3.750  -0.2800   0.01733   0.00814  -0.0193   0.9334   0.0418
  -3.500  -0.2483   0.01627   0.00712  -0.0200   0.9165   0.0653
  -3.250  -0.2194   0.01525   0.00650  -0.0204   0.8996   0.1396
  -3.000  -0.1934   0.01440   0.00607  -0.0202   0.8823   0.2412
  -2.750  -0.1690   0.01368   0.00573  -0.0195   0.8657   0.3557
  -2.500  -0.1462   0.01295   0.00549  -0.0183   0.8499   0.4958
  -2.250  -0.1220   0.01225   0.00535  -0.0168   0.8354   0.6575
  -2.000  -0.0652   0.01189   0.00535  -0.0207   0.8241   0.8462
  -1.750  -0.0082   0.01201   0.00525  -0.0254   0.8114   0.9213
  -1.500   0.0325   0.01216   0.00516  -0.0274   0.7972   0.9599
  -1.250   0.0803   0.01219   0.00492  -0.0313   0.7832   0.9857
  -1.000   0.1249   0.01212   0.00463  -0.0348   0.7689   1.0000
  -0.750   0.1478   0.01213   0.00447  -0.0338   0.7545   1.0000
  -0.500   0.1709   0.01216   0.00434  -0.0329   0.7405   1.0000
  -0.250   0.1942   0.01221   0.00424  -0.0320   0.7269   1.0000
   0.000   0.2181   0.01226   0.00417  -0.0312   0.7135   1.0000
   0.250   0.2420   0.01233   0.00412  -0.0304   0.7005   1.0000
   0.500   0.2660   0.01241   0.00409  -0.0296   0.6876   1.0000
   0.750   0.2900   0.01250   0.00408  -0.0288   0.6750   1.0000
   1.000   0.3141   0.01259   0.00408  -0.0280   0.6626   1.0000
   1.250   0.3382   0.01270   0.00410  -0.0272   0.6503   1.0000
   1.500   0.3624   0.01281   0.00414  -0.0264   0.6378   1.0000
   1.750   0.3868   0.01293   0.00421  -0.0256   0.6246   1.0000
   2.000   0.4112   0.01305   0.00431  -0.0249   0.6116   1.0000
   2.250   0.4356   0.01319   0.00440  -0.0242   0.5985   1.0000
   2.500   0.4600   0.01333   0.00451  -0.0234   0.5854   1.0000
   2.750   0.4843   0.01348   0.00463  -0.0227   0.5720   1.0000
   3.000   0.5087   0.01363   0.00479  -0.0219   0.5586   1.0000
   3.250   0.5330   0.01380   0.00494  -0.0211   0.5447   1.0000
   3.500   0.5573   0.01397   0.00511  -0.0204   0.5305   1.0000
   3.750   0.5815   0.01416   0.00529  -0.0196   0.5158   1.0000
   4.000   0.6056   0.01435   0.00552  -0.0188   0.5005   1.0000
   4.250   0.6297   0.01456   0.00574  -0.0180   0.4848   1.0000
   4.500   0.6536   0.01478   0.00598  -0.0172   0.4687   1.0000
   4.750   0.6774   0.01502   0.00623  -0.0164   0.4522   1.0000
   5.000   0.7009   0.01527   0.00653  -0.0156   0.4351   1.0000
   5.250   0.7244   0.01554   0.00685  -0.0147   0.4163   1.0000
   5.500   0.7475   0.01584   0.00718  -0.0139   0.3963   1.0000
   5.750   0.7702   0.01616   0.00752  -0.0129   0.3759   1.0000
   6.000   0.7927   0.01652   0.00795  -0.0120   0.3533   1.0000
   6.250   0.8148   0.01691   0.00837  -0.0111   0.3297   1.0000
   6.500   0.8362   0.01737   0.00882  -0.0101   0.3045   1.0000
   6.750   0.8571   0.01789   0.00933  -0.0090   0.2778   1.0000
   7.000   0.8774   0.01848   0.00994  -0.0080   0.2502   1.0000
   7.250   0.8970   0.01915   0.01059  -0.0068   0.2223   1.0000
   7.500   0.9158   0.01991   0.01133  -0.0057   0.1949   1.0000
   7.750   0.9334   0.02079   0.01213  -0.0045   0.1655   1.0000
   8.000   0.9497   0.02179   0.01301  -0.0033   0.1315   1.0000
   8.250   0.9649   0.02292   0.01399  -0.0020   0.1015   1.0000
   8.500   0.9801   0.02403   0.01511  -0.0006   0.0804   1.0000
   8.750   0.9928   0.02537   0.01636   0.0009   0.0620   1.0000
   9.000   1.0044   0.02679   0.01780   0.0027   0.0488   1.0000
   9.250   1.0138   0.02832   0.01937   0.0046   0.0416   1.0000
   9.500   1.0220   0.02987   0.02106   0.0066   0.0372   1.0000
   9.750   1.0294   0.03140   0.02272   0.0087   0.0343   1.0000
  10.000   1.0339   0.03304   0.02444   0.0108   0.0323   1.0000
  10.250   1.0338   0.03486   0.02631   0.0134   0.0307   1.0000
  10.500   1.0387   0.03647   0.02811   0.0152   0.0291   1.0000
  10.750   1.0427   0.03827   0.03010   0.0168   0.0275   1.0000
  11.000   1.0463   0.04023   0.03220   0.0179   0.0263   1.0000
  11.250   1.0494   0.04238   0.03447   0.0189   0.0254   1.0000
  11.500   1.0517   0.04472   0.03693   0.0196   0.0246   1.0000
  11.750   1.0540   0.04720   0.03951   0.0202   0.0241   1.0000
  12.000   1.0556   0.05000   0.04241   0.0208   0.0235   1.0000
  12.250   1.0572   0.05295   0.04552   0.0211   0.0232   1.0000
  12.500   1.0562   0.05617   0.04899   0.0211   0.0229   1.0000
  12.750   1.0527   0.05978   0.05284   0.0206   0.0227   1.0000
  13.000   1.0455   0.06393   0.05725   0.0196   0.0224   1.0000
  13.250   1.0359   0.06850   0.06206   0.0180   0.0222   1.0000
  13.500   1.0240   0.07358   0.06737   0.0158   0.0221   1.0000
  13.750   1.0109   0.07911   0.07310   0.0131   0.0221   1.0000
  14.000   0.9936   0.08565   0.07985   0.0095   0.0220   1.0000
  14.250   0.9749   0.09285   0.08724   0.0053   0.0221   1.0000
  14.500   0.9563   0.10056   0.09511   0.0007   0.0223   1.0000
  14.750   0.9344   0.10964   0.10433  -0.0050   0.0225   1.0000
  15.000   0.9127   0.11937   0.11417  -0.0108   0.0228   1.0000
  15.250   0.8897   0.13022   0.12509  -0.0172   0.0231   1.0000
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