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EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 1.5/9.0 (eh1590-il)
Reynolds number: 200,000
Max Cl/Cd: 58.74 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1590-il-200000-n5.txt
Download as CSV file: xf-eh1590-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5013   0.08535   0.08222  -0.0008   1.0000   0.0138
  -9.250  -0.5160   0.07660   0.07351  -0.0046   1.0000   0.0130
  -8.750  -0.6017   0.07281   0.06959  -0.0126   1.0000   0.0126
  -8.500  -0.6153   0.06731   0.06406  -0.0155   1.0000   0.0125
  -8.250  -0.6261   0.06174   0.05840  -0.0170   1.0000   0.0123
  -8.000  -0.6324   0.05602   0.05253  -0.0180   1.0000   0.0122
  -7.750  -0.6364   0.05001   0.04628  -0.0181   1.0000   0.0121
  -7.500  -0.6371   0.04420   0.04015  -0.0175   1.0000   0.0119
  -7.250  -0.6342   0.03877   0.03429  -0.0162   1.0000   0.0118
  -7.000  -0.6269   0.03399   0.02900  -0.0146   1.0000   0.0118
  -6.750  -0.6148   0.03010   0.02458  -0.0130   1.0000   0.0119
  -6.500  -0.5988   0.02697   0.02090  -0.0114   1.0000   0.0121
  -6.250  -0.5797   0.02456   0.01805  -0.0101   1.0000   0.0124
  -6.000  -0.5586   0.02268   0.01582  -0.0089   1.0000   0.0127
  -5.750  -0.5387   0.02026   0.01310  -0.0076   1.0000   0.0134
  -5.500  -0.5166   0.01908   0.01181  -0.0068   1.0000   0.0144
  -5.250  -0.4936   0.01839   0.01104  -0.0060   1.0000   0.0160
  -5.000  -0.4710   0.01740   0.00993  -0.0050   1.0000   0.0174
  -4.750  -0.4492   0.01634   0.00874  -0.0037   1.0000   0.0183
  -4.500  -0.4279   0.01546   0.00773  -0.0024   1.0000   0.0194
  -4.250  -0.3960   0.01434   0.00654  -0.0035   0.9867   0.0219
  -4.000  -0.3604   0.01364   0.00577  -0.0052   0.9685   0.0273
  -3.750  -0.3258   0.01304   0.00515  -0.0067   0.9465   0.0394
  -3.500  -0.2919   0.01247   0.00466  -0.0080   0.9222   0.0603
  -3.250  -0.2603   0.01204   0.00423  -0.0088   0.8957   0.0864
  -3.000  -0.2324   0.01167   0.00389  -0.0087   0.8678   0.1170
  -2.750  -0.2070   0.01130   0.00359  -0.0081   0.8407   0.1579
  -2.500  -0.1834   0.01088   0.00331  -0.0072   0.8150   0.2197
  -2.250  -0.1617   0.01027   0.00303  -0.0061   0.7906   0.3285
  -2.000  -0.1445   0.00932   0.00278  -0.0042   0.7684   0.5296
  -1.750  -0.1265   0.00874   0.00277  -0.0016   0.7477   0.7017
  -1.500  -0.1030   0.00863   0.00280   0.0001   0.7277   0.7850
  -1.250  -0.0772   0.00865   0.00280   0.0012   0.7083   0.8344
  -1.000  -0.0499   0.00874   0.00277   0.0020   0.6901   0.8679
  -0.750  -0.0208   0.00885   0.00278   0.0023   0.6720   0.8980
  -0.500   0.0125   0.00902   0.00285   0.0019   0.6543   0.9275
  -0.250   0.0569   0.00927   0.00295  -0.0008   0.6364   0.9505
   0.000   0.0967   0.00940   0.00292  -0.0031   0.6190   0.9599
   0.250   0.1303   0.00946   0.00285  -0.0043   0.6027   0.9654
   0.500   0.1633   0.00952   0.00279  -0.0054   0.5867   0.9706
   0.750   0.1984   0.00957   0.00273  -0.0070   0.5711   0.9746
   1.000   0.2312   0.00963   0.00269  -0.0082   0.5560   0.9798
   1.250   0.2646   0.00969   0.00266  -0.0094   0.5412   0.9842
   1.500   0.2989   0.00974   0.00265  -0.0110   0.5265   0.9882
   1.750   0.3320   0.00981   0.00265  -0.0122   0.5122   0.9928
   2.000   0.3658   0.00987   0.00265  -0.0136   0.4982   0.9968
   2.250   0.3975   0.00994   0.00267  -0.0147   0.4843   1.0000
   2.500   0.4206   0.01003   0.00274  -0.0139   0.4717   1.0000
   2.750   0.4438   0.01013   0.00281  -0.0130   0.4593   1.0000
   3.000   0.4670   0.01024   0.00291  -0.0122   0.4469   1.0000
   3.250   0.4902   0.01036   0.00301  -0.0114   0.4348   1.0000
   3.500   0.5134   0.01050   0.00314  -0.0106   0.4223   1.0000
   3.750   0.5367   0.01065   0.00331  -0.0098   0.4100   1.0000
   4.000   0.5601   0.01082   0.00347  -0.0090   0.3977   1.0000
   4.250   0.5835   0.01100   0.00366  -0.0082   0.3849   1.0000
   4.500   0.6069   0.01118   0.00386  -0.0074   0.3719   1.0000
   4.750   0.6304   0.01138   0.00408  -0.0067   0.3583   1.0000
   5.250   0.6775   0.01183   0.00461  -0.0051   0.3290   1.0000
   5.500   0.7010   0.01207   0.00489  -0.0044   0.3127   1.0000
   5.750   0.7243   0.01234   0.00520  -0.0036   0.2947   1.0000
   6.000   0.7466   0.01271   0.00549  -0.0028   0.2632   1.0000
   6.250   0.7668   0.01334   0.00589  -0.0018   0.2046   1.0000
   6.500   0.7866   0.01413   0.00641  -0.0009   0.1486   1.0000
   6.750   0.8044   0.01526   0.00718   0.0002   0.0841   1.0000
   7.000   0.8215   0.01652   0.00816   0.0014   0.0372   1.0000
   7.250   0.8408   0.01751   0.00915   0.0025   0.0243   1.0000
   7.500   0.8597   0.01853   0.01026   0.0037   0.0191   1.0000
   7.750   0.8800   0.01931   0.01118   0.0047   0.0163   1.0000
   8.000   0.8985   0.02031   0.01237   0.0058   0.0146   1.0000
   8.250   0.9139   0.02162   0.01381   0.0072   0.0133   1.0000
   8.500   0.9259   0.02328   0.01561   0.0090   0.0125   1.0000
   8.750   0.9417   0.02448   0.01695   0.0103   0.0119   1.0000
   9.000   0.9572   0.02568   0.01829   0.0117   0.0110   1.0000
   9.250   0.9723   0.02685   0.01958   0.0129   0.0100   1.0000
   9.500   0.9858   0.02814   0.02097   0.0142   0.0092   1.0000
   9.750   0.9969   0.02969   0.02265   0.0158   0.0088   1.0000
  10.000   1.0060   0.03141   0.02450   0.0174   0.0085   1.0000
  10.250   1.0118   0.03340   0.02662   0.0193   0.0082   1.0000
  10.500   1.0144   0.03565   0.02907   0.0214   0.0079   1.0000
  11.000   1.0128   0.04114   0.03497   0.0247   0.0077   1.0000
  11.250   1.0110   0.04372   0.03777   0.0255   0.0076   1.0000
  11.500   1.0070   0.04670   0.04097   0.0257   0.0076   1.0000
  11.750   1.0005   0.05015   0.04465   0.0252   0.0075   1.0000
  12.000   0.9918   0.05416   0.04889   0.0240   0.0075   1.0000
  12.250   0.9829   0.05840   0.05333   0.0222   0.0074   1.0000
  12.500   0.9724   0.06315   0.05827   0.0199   0.0074   1.0000
  12.750   0.9593   0.06865   0.06396   0.0169   0.0075   1.0000
  13.000   0.9470   0.07429   0.06977   0.0135   0.0075   1.0000
  13.250   0.9325   0.08064   0.07628   0.0096   0.0075   1.0000
  13.500   0.9173   0.08751   0.08331   0.0052   0.0075   1.0000
  13.750   0.9007   0.09502   0.09096   0.0006   0.0076   1.0000
  14.000   0.8854   0.10285   0.09890  -0.0043   0.0076   1.0000
  14.250   0.8683   0.11166   0.10783  -0.0096   0.0077   1.0000
  14.500   0.8509   0.12124   0.11751  -0.0153   0.0077   1.0000
  14.750   0.8401   0.12990   0.12628  -0.0203   0.0078   1.0000
  15.000   0.8099   0.14676   0.14319  -0.0286   0.0083   1.0000
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