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E207 (12.04%) (e207-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E207 (12.04%) (e207-il)
Reynolds number: 100,000
Max Cl/Cd: 53.29 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e207-il-100000-n5.txt
Download as CSV file: xf-e207-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E207  (12.04%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4645   0.08896   0.08398  -0.0373   1.0000   0.0300
 -10.000  -0.4733   0.08259   0.07767  -0.0407   1.0000   0.0300
  -9.750  -0.4845   0.07549   0.07062  -0.0449   1.0000   0.0297
  -9.500  -0.5037   0.06720   0.06236  -0.0512   1.0000   0.0291
  -9.250  -0.5288   0.06109   0.05620  -0.0555   1.0000   0.0288
  -9.000  -0.5529   0.05707   0.05214  -0.0551   1.0000   0.0285
  -8.750  -0.5709   0.05308   0.04798  -0.0541   1.0000   0.0284
  -8.500  -0.5840   0.04928   0.04394  -0.0523   1.0000   0.0284
  -8.250  -0.5918   0.04570   0.04007  -0.0502   1.0000   0.0285
  -8.000  -0.5955   0.04229   0.03633  -0.0478   1.0000   0.0286
  -7.750  -0.5952   0.03917   0.03280  -0.0453   1.0000   0.0288
  -7.500  -0.5912   0.03643   0.02970  -0.0428   1.0000   0.0290
  -7.250  -0.5844   0.03403   0.02694  -0.0403   1.0000   0.0293
  -7.000  -0.5666   0.03154   0.02401  -0.0397   0.9967   0.0299
  -6.750  -0.5332   0.02908   0.02107  -0.0417   0.9877   0.0311
  -6.500  -0.4999   0.02727   0.01917  -0.0440   0.9783   0.0333
  -6.250  -0.4645   0.02567   0.01736  -0.0460   0.9690   0.0352
  -6.000  -0.4310   0.02408   0.01553  -0.0474   0.9578   0.0366
  -5.750  -0.3980   0.02268   0.01396  -0.0485   0.9457   0.0384
  -5.500  -0.3653   0.02151   0.01260  -0.0495   0.9328   0.0403
  -5.250  -0.3342   0.02032   0.01141  -0.0505   0.9190   0.0439
  -5.000  -0.3015   0.01950   0.01044  -0.0516   0.9049   0.0505
  -4.750  -0.2702   0.01851   0.00942  -0.0524   0.8904   0.0593
  -4.500  -0.2395   0.01760   0.00849  -0.0530   0.8753   0.0778
  -4.250  -0.2100   0.01679   0.00778  -0.0535   0.8598   0.1134
  -4.000  -0.1822   0.01602   0.00725  -0.0537   0.8440   0.1769
  -3.750  -0.1569   0.01522   0.00685  -0.0536   0.8284   0.2687
  -3.500  -0.1317   0.01466   0.00656  -0.0531   0.8132   0.3535
  -3.250  -0.1062   0.01433   0.00636  -0.0525   0.7987   0.4269
  -3.000  -0.0808   0.01410   0.00617  -0.0517   0.7847   0.4882
  -2.750  -0.0553   0.01392   0.00602  -0.0509   0.7713   0.5394
  -2.500  -0.0297   0.01378   0.00589  -0.0501   0.7588   0.5835
  -2.250  -0.0038   0.01366   0.00577  -0.0493   0.7472   0.6237
  -2.000   0.0224   0.01356   0.00564  -0.0485   0.7364   0.6629
  -1.750   0.0487   0.01347   0.00556  -0.0478   0.7255   0.7018
  -1.500   0.0752   0.01341   0.00550  -0.0470   0.7151   0.7410
  -1.250   0.1028   0.01336   0.00544  -0.0464   0.7057   0.7816
  -1.000   0.1328   0.01336   0.00542  -0.0462   0.6963   0.8232
  -0.750   0.1685   0.01339   0.00542  -0.0472   0.6869   0.8629
  -0.500   0.2084   0.01346   0.00537  -0.0492   0.6785   0.8980
  -0.250   0.2495   0.01355   0.00537  -0.0517   0.6691   0.9272
   0.000   0.2908   0.01364   0.00532  -0.0543   0.6606   0.9516
   0.250   0.3323   0.01372   0.00527  -0.0572   0.6522   0.9718
   0.500   0.3757   0.01377   0.00522  -0.0606   0.6437   0.9885
   0.750   0.4142   0.01382   0.00515  -0.0631   0.6361   1.0000
   1.000   0.4356   0.01394   0.00521  -0.0622   0.6281   1.0000
   1.250   0.4581   0.01408   0.00523  -0.0613   0.6215   1.0000
   1.500   0.4803   0.01423   0.00536  -0.0604   0.6136   1.0000
   1.750   0.5036   0.01439   0.00543  -0.0596   0.6073   1.0000
   2.000   0.5264   0.01457   0.00560  -0.0588   0.5998   1.0000
   2.250   0.5500   0.01475   0.00572  -0.0580   0.5933   1.0000
   2.500   0.5732   0.01495   0.00592  -0.0572   0.5863   1.0000
   2.750   0.5969   0.01515   0.00609  -0.0565   0.5797   1.0000
   3.000   0.6205   0.01536   0.00631  -0.0557   0.5730   1.0000
   3.250   0.6441   0.01558   0.00654  -0.0549   0.5661   1.0000
   3.500   0.6681   0.01580   0.00676  -0.0542   0.5597   1.0000
   3.750   0.6915   0.01603   0.00704  -0.0535   0.5525   1.0000
   4.000   0.7159   0.01626   0.00726  -0.0528   0.5461   1.0000
   4.250   0.7391   0.01650   0.00760  -0.0520   0.5381   1.0000
   4.500   0.7633   0.01672   0.00783  -0.0513   0.5311   1.0000
   4.750   0.7867   0.01695   0.00813  -0.0505   0.5225   1.0000
   5.000   0.8102   0.01718   0.00842  -0.0497   0.5140   1.0000
   5.250   0.8342   0.01737   0.00867  -0.0489   0.5054   1.0000
   5.500   0.8568   0.01760   0.00901  -0.0479   0.4951   1.0000
   5.750   0.8799   0.01780   0.00928  -0.0470   0.4850   1.0000
   6.000   0.9033   0.01797   0.00949  -0.0461   0.4746   1.0000
   6.250   0.9256   0.01817   0.00980  -0.0451   0.4626   1.0000
   6.500   0.9475   0.01839   0.01015  -0.0440   0.4498   1.0000
   6.750   0.9693   0.01860   0.01046  -0.0429   0.4360   1.0000
   7.000   0.9905   0.01882   0.01077  -0.0417   0.4209   1.0000
   7.250   1.0112   0.01906   0.01107  -0.0404   0.4042   1.0000
   7.500   1.0307   0.01935   0.01147  -0.0390   0.3845   1.0000
   7.750   1.0492   0.01969   0.01188  -0.0374   0.3624   1.0000
   8.000   1.0664   0.02012   0.01235  -0.0357   0.3359   1.0000
   8.250   1.0814   0.02068   0.01286  -0.0338   0.3053   1.0000
   8.500   1.0941   0.02140   0.01351  -0.0316   0.2708   1.0000
   8.750   1.1032   0.02237   0.01432  -0.0291   0.2354   1.0000
   9.000   1.1101   0.02348   0.01530  -0.0264   0.2038   1.0000
   9.250   1.1154   0.02469   0.01644  -0.0236   0.1774   1.0000
   9.500   1.1186   0.02591   0.01759  -0.0205   0.1551   1.0000
   9.750   1.1192   0.02724   0.01887  -0.0173   0.1378   1.0000
  10.000   1.1205   0.02866   0.02027  -0.0146   0.1221   1.0000
  10.250   1.1210   0.03024   0.02184  -0.0121   0.1083   1.0000
  10.500   1.1206   0.03202   0.02361  -0.0100   0.0968   1.0000
  10.750   1.1200   0.03397   0.02556  -0.0083   0.0855   1.0000
  11.000   1.1201   0.03603   0.02764  -0.0070   0.0742   1.0000
  11.250   1.1202   0.03824   0.02987  -0.0060   0.0637   1.0000
  11.500   1.1200   0.04059   0.03226  -0.0052   0.0557   1.0000
  11.750   1.1170   0.04335   0.03500  -0.0047   0.0487   1.0000
  12.000   1.1171   0.04592   0.03773  -0.0043   0.0426   1.0000
  12.250   1.1123   0.04908   0.04090  -0.0041   0.0392   1.0000
  12.500   1.1122   0.05186   0.04383  -0.0040   0.0342   1.0000
  12.750   1.1079   0.05521   0.04722  -0.0042   0.0309   1.0000
  13.000   1.1040   0.05857   0.05067  -0.0044   0.0284   1.0000
  13.250   1.1021   0.06177   0.05403  -0.0046   0.0263   1.0000
  13.500   1.0989   0.06525   0.05762  -0.0050   0.0245   1.0000
  13.750   1.0954   0.06883   0.06129  -0.0057   0.0234   1.0000
  14.000   1.0907   0.07265   0.06518  -0.0064   0.0225   1.0000
  14.250   1.0889   0.07618   0.06884  -0.0069   0.0215   1.0000
  14.500   1.0883   0.07968   0.07252  -0.0074   0.0206   1.0000
  14.750   1.0874   0.08331   0.07632  -0.0081   0.0200   1.0000
  15.000   1.0851   0.08730   0.08048  -0.0092   0.0193   1.0000
  15.250   1.0816   0.09156   0.08489  -0.0106   0.0187   1.0000
  15.500   1.0773   0.09607   0.08955  -0.0123   0.0182   1.0000
  15.750   1.0719   0.10090   0.09451  -0.0144   0.0176   1.0000
  16.000   1.0659   0.10591   0.09962  -0.0166   0.0171   1.0000
  16.500   1.0535   0.11645   0.11048  -0.0216   0.0167   1.0000
  16.750   1.0430   0.12289   0.11705  -0.0250   0.0162   1.0000
  17.000   1.0332   0.12950   0.12383  -0.0286   0.0162   1.0000
  17.250   1.0165   0.13819   0.13275  -0.0338   0.0159   1.0000
  17.500   1.0066   0.14531   0.14000  -0.0378   0.0162   1.0000
  17.750   0.9911   0.15439   0.14919  -0.0432   0.0163   1.0000
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