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EPPLER 862 STRUT AIRFOIL (e862-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 862 STRUT AIRFOIL (e862-il)
Reynolds number: 200,000
Max Cl/Cd: 32.66 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e862-il-200000-n5.txt
Download as CSV file: xf-e862-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 862 STRUT AIRFOIL                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.8593   0.10487   0.09891  -0.0040   0.8259   0.2306
 -16.250  -0.8332   0.10565   0.09950  -0.0032   0.7721   0.2312
 -15.750  -0.8700   0.09492   0.08848  -0.0053   0.7392   0.2439
 -15.500  -0.8394   0.09575   0.08922  -0.0052   0.7145   0.2445
 -15.000  -0.8796   0.08474   0.07798  -0.0073   0.6943   0.2576
 -14.000  -0.8381   0.07780   0.07076  -0.0090   0.6446   0.2705
 -13.500  -0.9158   0.06346   0.05614  -0.0107   0.6362   0.2864
 -13.250  -0.8805   0.06449   0.05715  -0.0108   0.6246   0.2873
 -13.000  -0.8464   0.06538   0.05804  -0.0110   0.6132   0.2883
 -12.500  -0.9149   0.05296   0.04534  -0.0119   0.6052   0.3023
 -12.250  -0.8831   0.05352   0.04590  -0.0121   0.5961   0.3037
 -12.000  -0.8608   0.05315   0.04552  -0.0123   0.5878   0.3059
 -11.750  -0.9613   0.04156   0.03358  -0.0119   0.5892   0.3168
 -11.500  -0.9318   0.04180   0.03384  -0.0121   0.5811   0.3185
 -11.250  -0.9106   0.04135   0.03335  -0.0122   0.5748   0.3207
 -11.000  -0.9076   0.03934   0.03130  -0.0121   0.5697   0.3241
 -10.750  -0.9316   0.03532   0.02710  -0.0114   0.5660   0.3293
 -10.500  -0.9404   0.03272   0.02434  -0.0107   0.5615   0.3329
 -10.250  -0.9162   0.03248   0.02410  -0.0108   0.5557   0.3349
 -10.000  -0.8998   0.03177   0.02332  -0.0106   0.5508   0.3373
  -9.750  -0.8905   0.03059   0.02211  -0.0101   0.5462   0.3402
  -9.500  -0.8871   0.02916   0.02057  -0.0091   0.5416   0.3434
  -9.250  -0.8885   0.02764   0.01888  -0.0075   0.5374   0.3467
  -9.000  -0.8761   0.02687   0.01804  -0.0065   0.5331   0.3492
  -8.750  -0.8526   0.02665   0.01781  -0.0064   0.5289   0.3512
  -8.500  -0.8338   0.02627   0.01739  -0.0058   0.5253   0.3533
  -8.250  -0.8180   0.02579   0.01689  -0.0048   0.5216   0.3557
  -8.000  -0.8070   0.02531   0.01636  -0.0030   0.5179   0.3583
  -7.750  -0.7994   0.02486   0.01582  -0.0006   0.5144   0.3610
  -7.500  -0.7881   0.02438   0.01519   0.0013   0.5108   0.3637
  -7.250  -0.7677   0.02409   0.01482   0.0020   0.5072   0.3658
  -6.750  -0.7180   0.02383   0.01457   0.0023   0.5005   0.3697
  -6.500  -0.6948   0.02365   0.01439   0.0027   0.4973   0.3719
  -6.250  -0.6720   0.02344   0.01414   0.0031   0.4941   0.3743
  -6.000  -0.6495   0.02320   0.01384   0.0035   0.4910   0.3767
  -5.750  -0.6278   0.02295   0.01348   0.0041   0.4880   0.3794
  -5.500  -0.6066   0.02268   0.01307   0.0047   0.4850   0.3819
  -5.250  -0.5788   0.02258   0.01295   0.0045   0.4820   0.3837
  -5.000  -0.5513   0.02248   0.01288   0.0043   0.4792   0.3855
  -4.750  -0.5244   0.02238   0.01280   0.0042   0.4765   0.3875
  -4.500  -0.4978   0.02228   0.01271   0.0041   0.4737   0.3897
  -4.250  -0.4715   0.02216   0.01257   0.0040   0.4709   0.3921
  -4.000  -0.4455   0.02202   0.01238   0.0040   0.4681   0.3945
  -3.750  -0.4195   0.02187   0.01214   0.0040   0.4654   0.3969
  -3.500  -0.3938   0.02172   0.01188   0.0041   0.4628   0.3992
  -3.250  -0.3663   0.02163   0.01173   0.0039   0.4603   0.4012
  -3.000  -0.3377   0.02158   0.01173   0.0035   0.4580   0.4032
  -2.750  -0.3094   0.02153   0.01173   0.0032   0.4557   0.4052
  -2.500  -0.2814   0.02148   0.01170   0.0029   0.4531   0.4072
  -2.250  -0.2535   0.02142   0.01164   0.0027   0.4505   0.4093
  -2.000  -0.2256   0.02134   0.01154   0.0024   0.4478   0.4116
  -1.750  -0.1979   0.02127   0.01143   0.0022   0.4453   0.4140
  -1.500  -0.1702   0.02121   0.01129   0.0020   0.4430   0.4166
  -1.250  -0.1426   0.02117   0.01114   0.0017   0.4409   0.4189
  -1.000  -0.1136   0.02116   0.01112   0.0013   0.4389   0.4208
  -0.750  -0.0850   0.02113   0.01118   0.0010   0.4368   0.4227
  -0.500  -0.0566   0.02112   0.01123   0.0006   0.4344   0.4247
  -0.250  -0.0283   0.02112   0.01126   0.0003   0.4318   0.4268
   0.000   0.0000   0.02112   0.01127   0.0000   0.4292   0.4292
   0.250   0.0283   0.02112   0.01126  -0.0003   0.4268   0.4318
   0.500   0.0566   0.02112   0.01123  -0.0006   0.4247   0.4344
   0.750   0.0850   0.02113   0.01118  -0.0010   0.4227   0.4368
   1.000   0.1136   0.02116   0.01112  -0.0013   0.4208   0.4389
   1.250   0.1426   0.02117   0.01114  -0.0017   0.4189   0.4409
   1.500   0.1703   0.02121   0.01129  -0.0020   0.4166   0.4430
   1.750   0.1979   0.02127   0.01143  -0.0022   0.4140   0.4453
   2.000   0.2256   0.02134   0.01154  -0.0024   0.4116   0.4478
   2.250   0.2535   0.02142   0.01164  -0.0027   0.4093   0.4505
   2.500   0.2814   0.02148   0.01170  -0.0029   0.4072   0.4531
   2.750   0.3095   0.02153   0.01173  -0.0032   0.4052   0.4556
   3.000   0.3377   0.02158   0.01173  -0.0035   0.4032   0.4580
   3.250   0.3664   0.02163   0.01173  -0.0039   0.4012   0.4603
   3.500   0.3939   0.02172   0.01188  -0.0041   0.3992   0.4628
   3.750   0.4196   0.02186   0.01214  -0.0040   0.3969   0.4654
   4.000   0.4455   0.02202   0.01238  -0.0040   0.3946   0.4681
   4.250   0.4716   0.02216   0.01257  -0.0041   0.3921   0.4709
   4.500   0.4979   0.02228   0.01271  -0.0041   0.3897   0.4737
   4.750   0.5245   0.02237   0.01280  -0.0042   0.3875   0.4765
   5.000   0.5514   0.02248   0.01288  -0.0043   0.3855   0.4792
   5.250   0.5790   0.02258   0.01295  -0.0045   0.3837   0.4820
   5.500   0.6067   0.02268   0.01307  -0.0047   0.3819   0.4850
   5.750   0.6280   0.02295   0.01348  -0.0041   0.3794   0.4880
   6.000   0.6498   0.02320   0.01384  -0.0036   0.3767   0.4910
   6.250   0.6722   0.02344   0.01414  -0.0031   0.3743   0.4941
   6.500   0.6951   0.02365   0.01438  -0.0027   0.3719   0.4973
   6.750   0.7184   0.02383   0.01457  -0.0024   0.3697   0.5005
   7.250   0.7681   0.02409   0.01482  -0.0021   0.3658   0.5072
   7.500   0.7886   0.02438   0.01518  -0.0014   0.3637   0.5108
   7.750   0.8000   0.02486   0.01582   0.0004   0.3610   0.5144
   8.000   0.8079   0.02531   0.01636   0.0029   0.3582   0.5179
   8.250   0.8189   0.02578   0.01688   0.0047   0.3557   0.5216
   8.500   0.8347   0.02626   0.01738   0.0056   0.3533   0.5253
   8.750   0.8536   0.02664   0.01779   0.0062   0.3511   0.5290
   9.000   0.8772   0.02686   0.01802   0.0063   0.3492   0.5331
   9.250   0.8896   0.02762   0.01887   0.0073   0.3467   0.5374
   9.500   0.8884   0.02913   0.02055   0.0090   0.3434   0.5417
   9.750   0.8921   0.03056   0.02207   0.0099   0.3402   0.5463
  10.000   0.9015   0.03173   0.02328   0.0104   0.3373   0.5509
  10.250   0.9179   0.03244   0.02406   0.0106   0.3349   0.5558
  10.500   0.9422   0.03268   0.02430   0.0104   0.3329   0.5616
  10.750   0.9338   0.03525   0.02703   0.0112   0.3293   0.5661
  11.000   0.9103   0.03924   0.03120   0.0119   0.3242   0.5699
  11.250   0.9133   0.04125   0.03325   0.0119   0.3207   0.5749
  11.500   0.9342   0.04173   0.03376   0.0118   0.3185   0.5812
  11.750   0.9638   0.04148   0.03351   0.0116   0.3168   0.5894
  12.250   0.8862   0.05341   0.04579   0.0118   0.3038   0.5964
  12.500   0.9178   0.05286   0.04524   0.0116   0.3024   0.6055
  13.000   0.8494   0.06529   0.05796   0.0106   0.2883   0.6136
  13.250   0.8835   0.06441   0.05707   0.0105   0.2873   0.6249
  13.500   0.9188   0.06338   0.05607   0.0104   0.2864   0.6365
  14.000   0.7637   0.08691   0.07995   0.0075   0.2609   0.6348
  14.250   0.7906   0.08674   0.07983   0.0072   0.2599   0.6474
  14.500   0.8190   0.08636   0.07950   0.0070   0.2590   0.6605
  14.750   0.8500   0.08565   0.07883   0.0069   0.2583   0.6765
  15.000   0.8830   0.08466   0.07790   0.0069   0.2576   0.6950
  15.500   0.8426   0.09569   0.08917   0.0048   0.2446   0.7152
  15.750   0.8732   0.09487   0.08843   0.0048   0.2439   0.7401
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