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EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EH 1.5/9.0 (eh1590-il)
Reynolds number: 50,000
Max Cl/Cd: 32.28 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1590-il-50000-n5.txt
Download as CSV file: xf-eh1590-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5600   0.09587   0.08925  -0.0020   1.0000   0.0461
  -8.750  -0.5638   0.09059   0.08405  -0.0056   1.0000   0.0448
  -8.500  -0.5721   0.08455   0.07808  -0.0108   1.0000   0.0434
  -8.000  -0.5962   0.07282   0.06614  -0.0177   1.0000   0.0405
  -7.750  -0.5963   0.06843   0.06167  -0.0183   1.0000   0.0402
  -7.500  -0.5947   0.06412   0.05721  -0.0186   1.0000   0.0400
  -7.250  -0.5915   0.05980   0.05269  -0.0187   1.0000   0.0398
  -7.000  -0.5861   0.05552   0.04814  -0.0184   1.0000   0.0397
  -6.750  -0.5783   0.05137   0.04365  -0.0179   1.0000   0.0397
  -6.500  -0.5681   0.04733   0.03919  -0.0171   1.0000   0.0398
  -6.250  -0.5551   0.04352   0.03490  -0.0160   1.0000   0.0401
  -6.000  -0.5403   0.04003   0.03097  -0.0149   1.0000   0.0415
  -5.750  -0.5227   0.03786   0.02870  -0.0142   1.0000   0.0447
  -5.500  -0.5033   0.03537   0.02583  -0.0132   1.0000   0.0480
  -5.250  -0.4816   0.03257   0.02251  -0.0120   1.0000   0.0503
  -5.000  -0.4573   0.03000   0.01938  -0.0108   1.0000   0.0528
  -4.750  -0.4347   0.02816   0.01746  -0.0101   1.0000   0.0585
  -4.500  -0.4097   0.02646   0.01549  -0.0091   1.0000   0.0675
  -4.250  -0.3845   0.02485   0.01379  -0.0082   1.0000   0.0763
  -4.000  -0.3604   0.02359   0.01248  -0.0073   1.0000   0.0942
  -3.750  -0.3368   0.02231   0.01122  -0.0064   1.0000   0.1149
  -3.500  -0.3148   0.02117   0.01015  -0.0054   1.0000   0.1479
  -3.250  -0.2957   0.01997   0.00921  -0.0042   1.0000   0.1958
  -3.000  -0.2807   0.01863   0.00843  -0.0025   1.0000   0.2804
  -2.750  -0.2749   0.01671   0.00813   0.0016   1.0000   0.5467
  -2.500  -0.2209   0.01671   0.00871   0.0015   1.0000   0.8763
  -2.250  -0.1111   0.01708   0.00826  -0.0117   1.0000   0.9696
  -2.000  -0.0351   0.01670   0.00741  -0.0215   1.0000   1.0000
  -1.750  -0.0213   0.01659   0.00722  -0.0200   1.0000   1.0000
  -1.500  -0.0119   0.01658   0.00716  -0.0178   1.0000   1.0000
  -1.250   0.0090   0.01662   0.00709  -0.0179   0.9847   1.0000
  -1.000   0.0576   0.01662   0.00689  -0.0228   0.9505   1.0000
  -0.750   0.1041   0.01660   0.00668  -0.0269   0.9182   1.0000
  -0.500   0.1450   0.01657   0.00646  -0.0296   0.8868   1.0000
  -0.250   0.1774   0.01660   0.00632  -0.0305   0.8565   1.0000
   0.000   0.2036   0.01668   0.00624  -0.0300   0.8281   1.0000
   0.250   0.2268   0.01679   0.00621  -0.0289   0.8025   1.0000
   0.500   0.2483   0.01694   0.00622  -0.0275   0.7781   1.0000
   0.750   0.2695   0.01710   0.00626  -0.0261   0.7559   1.0000
   1.000   0.2907   0.01728   0.00633  -0.0247   0.7351   1.0000
   1.250   0.3120   0.01747   0.00643  -0.0233   0.7154   1.0000
   1.500   0.3334   0.01769   0.00659  -0.0220   0.6962   1.0000
   1.750   0.3551   0.01790   0.00673  -0.0206   0.6785   1.0000
   2.000   0.3769   0.01814   0.00691  -0.0194   0.6611   1.0000
   2.250   0.3989   0.01840   0.00715  -0.0182   0.6438   1.0000
   2.500   0.4210   0.01867   0.00744  -0.0171   0.6271   1.0000
   2.750   0.4433   0.01895   0.00771  -0.0159   0.6112   1.0000
   3.000   0.4657   0.01924   0.00799  -0.0148   0.5956   1.0000
   3.250   0.4882   0.01954   0.00831  -0.0137   0.5804   1.0000
   3.500   0.5112   0.01987   0.00865  -0.0127   0.5653   1.0000
   3.750   0.5341   0.02022   0.00913  -0.0118   0.5497   1.0000
   4.000   0.5569   0.02059   0.00957  -0.0108   0.5344   1.0000
   4.250   0.5796   0.02097   0.01004  -0.0099   0.5191   1.0000
   4.500   0.6024   0.02137   0.01053  -0.0089   0.5039   1.0000
   4.750   0.6252   0.02178   0.01105  -0.0079   0.4887   1.0000
   5.000   0.6479   0.02220   0.01165  -0.0069   0.4734   1.0000
   5.250   0.6707   0.02263   0.01221  -0.0059   0.4581   1.0000
   5.500   0.6934   0.02306   0.01277  -0.0048   0.4426   1.0000
   5.750   0.7161   0.02349   0.01334  -0.0037   0.4269   1.0000
   6.000   0.7380   0.02401   0.01408  -0.0027   0.4092   1.0000
   6.250   0.7599   0.02450   0.01483  -0.0016   0.3912   1.0000
   6.500   0.7818   0.02493   0.01542  -0.0004   0.3728   1.0000
   6.750   0.8025   0.02542   0.01616   0.0008   0.3509   1.0000
   7.000   0.8221   0.02578   0.01670   0.0023   0.3249   1.0000
   7.250   0.8376   0.02595   0.01694   0.0042   0.2825   1.0000
   7.500   0.8493   0.02654   0.01734   0.0060   0.2174   1.0000
   7.750   0.8577   0.02821   0.01859   0.0076   0.1412   1.0000
   8.000   0.8608   0.03097   0.02083   0.0093   0.0893   1.0000
   8.250   0.8658   0.03347   0.02318   0.0110   0.0680   1.0000
   8.500   0.8711   0.03578   0.02561   0.0128   0.0595   1.0000
   8.750   0.8762   0.03800   0.02788   0.0145   0.0529   1.0000
   9.000   0.8824   0.04017   0.03021   0.0161   0.0474   1.0000
   9.250   0.8882   0.04228   0.03244   0.0175   0.0431   1.0000
   9.500   0.8922   0.04456   0.03475   0.0192   0.0406   1.0000
   9.750   0.9035   0.04693   0.03732   0.0208   0.0389   1.0000
  10.000   0.9156   0.04955   0.04027   0.0222   0.0373   1.0000
  10.250   0.9233   0.05251   0.04355   0.0234   0.0361   1.0000
  10.500   0.9250   0.05564   0.04697   0.0241   0.0351   1.0000
  10.750   0.9221   0.05908   0.05068   0.0242   0.0341   1.0000
  11.000   0.9158   0.06287   0.05470   0.0236   0.0333   1.0000
  11.250   0.9073   0.06714   0.05919   0.0223   0.0329   1.0000
  11.500   0.8962   0.07191   0.06417   0.0201   0.0325   1.0000
  11.750   0.8819   0.07764   0.07010   0.0170   0.0326   1.0000
  12.000   0.8649   0.08428   0.07692   0.0129   0.0328   1.0000
  12.250   0.8421   0.09287   0.08572   0.0073   0.0343   1.0000
  12.500   0.8213   0.10179   0.09476   0.0017   0.0354   1.0000
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