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EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EH 1.5/9.0 (eh1590-il)
Reynolds number: 100,000
Max Cl/Cd: 45.53 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1590-il-100000-n5.txt
Download as CSV file: xf-eh1590-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.5/9.0                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5707   0.08909   0.08441  -0.0023   1.0000   0.0228
  -8.750  -0.5781   0.08288   0.07826  -0.0068   1.0000   0.0220
  -8.500  -0.5915   0.07561   0.07105  -0.0131   1.0000   0.0213
  -8.250  -0.6089   0.06737   0.06276  -0.0171   1.0000   0.0203
  -7.750  -0.6137   0.05719   0.05215  -0.0187   1.0000   0.0198
  -7.500  -0.6133   0.05261   0.04733  -0.0185   1.0000   0.0197
  -7.250  -0.6101   0.04807   0.04243  -0.0178   1.0000   0.0196
  -7.000  -0.6037   0.04375   0.03771  -0.0169   1.0000   0.0197
  -6.750  -0.5958   0.03946   0.03302  -0.0157   1.0000   0.0201
  -6.500  -0.5825   0.03687   0.03023  -0.0149   1.0000   0.0214
  -6.250  -0.5653   0.03497   0.02812  -0.0141   1.0000   0.0231
  -6.000  -0.5482   0.03215   0.02488  -0.0128   1.0000   0.0243
  -5.750  -0.5294   0.02915   0.02139  -0.0114   1.0000   0.0248
  -5.500  -0.5085   0.02662   0.01842  -0.0101   1.0000   0.0255
  -5.250  -0.4861   0.02445   0.01588  -0.0089   1.0000   0.0266
  -5.000  -0.4629   0.02263   0.01376  -0.0077   1.0000   0.0280
  -4.750  -0.4401   0.02107   0.01201  -0.0066   1.0000   0.0297
  -4.500  -0.4188   0.01997   0.01089  -0.0056   1.0000   0.0346
  -4.250  -0.3969   0.01897   0.00976  -0.0044   1.0000   0.0398
  -4.000  -0.3770   0.01785   0.00866  -0.0030   1.0000   0.0460
  -3.750  -0.3569   0.01709   0.00792  -0.0016   1.0000   0.0582
  -3.500  -0.3376   0.01633   0.00720  -0.0002   1.0000   0.0744
  -3.250  -0.3103   0.01560   0.00657  -0.0004   0.9918   0.1025
  -3.000  -0.2726   0.01482   0.00596  -0.0029   0.9735   0.1519
  -2.750  -0.2368   0.01392   0.00547  -0.0050   0.9539   0.2423
  -2.500  -0.2091   0.01241   0.00509  -0.0055   0.9318   0.4931
  -2.250  -0.1778   0.01170   0.00533  -0.0044   0.9132   0.7624
  -2.000  -0.1392   0.01179   0.00536  -0.0050   0.8917   0.8467
  -1.750  -0.0987   0.01195   0.00534  -0.0062   0.8689   0.8907
  -1.500  -0.0563   0.01213   0.00529  -0.0080   0.8451   0.9228
  -1.250   0.0097   0.01241   0.00528  -0.0143   0.8222   0.9588
  -1.000   0.0686   0.01246   0.00506  -0.0200   0.7965   0.9813
  -0.750   0.1062   0.01237   0.00476  -0.0220   0.7702   0.9886
  -0.500   0.1413   0.01232   0.00448  -0.0236   0.7459   0.9958
  -0.250   0.1714   0.01228   0.00428  -0.0242   0.7230   1.0000
   0.000   0.1932   0.01229   0.00414  -0.0232   0.7025   1.0000
   0.250   0.2150   0.01231   0.00404  -0.0221   0.6828   1.0000
   0.500   0.2369   0.01235   0.00395  -0.0210   0.6647   1.0000
   0.750   0.2595   0.01241   0.00389  -0.0201   0.6474   1.0000
   1.000   0.2821   0.01248   0.00387  -0.0192   0.6303   1.0000
   1.250   0.3046   0.01256   0.00387  -0.0183   0.6141   1.0000
   1.500   0.3271   0.01266   0.00391  -0.0173   0.5985   1.0000
   1.750   0.3498   0.01278   0.00395  -0.0164   0.5835   1.0000
   2.000   0.3725   0.01290   0.00402  -0.0154   0.5688   1.0000
   2.250   0.3953   0.01304   0.00411  -0.0145   0.5545   1.0000
   2.500   0.4182   0.01319   0.00425  -0.0136   0.5404   1.0000
   2.750   0.4412   0.01336   0.00439  -0.0127   0.5265   1.0000
   3.000   0.4643   0.01353   0.00454  -0.0118   0.5127   1.0000
   3.250   0.4875   0.01372   0.00473  -0.0110   0.4992   1.0000
   3.500   0.5107   0.01392   0.00493  -0.0101   0.4856   1.0000
   3.750   0.5340   0.01413   0.00519  -0.0093   0.4721   1.0000
   4.000   0.5573   0.01435   0.00544  -0.0084   0.4585   1.0000
   4.250   0.5806   0.01459   0.00571  -0.0076   0.4449   1.0000
   4.500   0.6040   0.01484   0.00600  -0.0068   0.4312   1.0000
   4.750   0.6273   0.01510   0.00632  -0.0059   0.4173   1.0000
   5.000   0.6506   0.01537   0.00670  -0.0051   0.4031   1.0000
   5.250   0.6739   0.01566   0.00706  -0.0042   0.3886   1.0000
   5.500   0.6970   0.01596   0.00744  -0.0034   0.3734   1.0000
   5.750   0.7201   0.01628   0.00783  -0.0025   0.3576   1.0000
   6.000   0.7433   0.01661   0.00829  -0.0017   0.3397   1.0000
   6.250   0.7661   0.01695   0.00879  -0.0009   0.3204   1.0000
   6.500   0.7881   0.01731   0.00921   0.0001   0.2934   1.0000
   6.750   0.8074   0.01783   0.00956   0.0011   0.2372   1.0000
   7.000   0.8255   0.01875   0.01019   0.0021   0.1708   1.0000
   7.250   0.8401   0.02031   0.01129   0.0033   0.0922   1.0000
   7.500   0.8521   0.02232   0.01291   0.0049   0.0449   1.0000
   7.750   0.8673   0.02384   0.01448   0.0063   0.0342   1.0000
   8.000   0.8801   0.02554   0.01635   0.0079   0.0294   1.0000
   8.250   0.8942   0.02697   0.01800   0.0095   0.0272   1.0000
   8.500   0.9078   0.02838   0.01959   0.0110   0.0245   1.0000
   8.750   0.9198   0.02988   0.02118   0.0125   0.0216   1.0000
   9.000   0.9265   0.03202   0.02340   0.0144   0.0200   1.0000
   9.250   0.9383   0.03381   0.02532   0.0160   0.0193   1.0000
   9.500   0.9508   0.03573   0.02743   0.0175   0.0187   1.0000
   9.750   0.9628   0.03787   0.02978   0.0190   0.0181   1.0000
  10.000   0.9734   0.04027   0.03242   0.0204   0.0176   1.0000
  10.250   0.9808   0.04285   0.03527   0.0219   0.0171   1.0000
  10.500   0.9830   0.04533   0.03800   0.0236   0.0167   1.0000
  10.750   0.9812   0.04786   0.04076   0.0251   0.0160   1.0000
  11.000   0.9772   0.05077   0.04390   0.0259   0.0156   1.0000
  11.250   0.9714   0.05381   0.04716   0.0260   0.0152   1.0000
  11.500   0.9632   0.05744   0.05108   0.0253   0.0150   1.0000
  11.750   0.9541   0.06117   0.05497   0.0237   0.0145   1.0000
  12.000   0.9424   0.06585   0.05985   0.0215   0.0143   1.0000
  12.250   0.9296   0.07103   0.06523   0.0186   0.0143   1.0000
  12.500   0.9139   0.07715   0.07155   0.0149   0.0145   1.0000
  12.750   0.8922   0.08501   0.07958   0.0099   0.0150   1.0000
  13.000   0.8693   0.09375   0.08850   0.0040   0.0155   1.0000
  13.250   0.8419   0.10447   0.09937  -0.0030   0.0164   1.0000
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