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EPPLER 637 AIRFOIL (e637-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 637 AIRFOIL (e637-il)
Reynolds number: 50,000
Max Cl/Cd: 14.86 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e637-il-50000.txt
Download as CSV file: xf-e637-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 637 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3995   0.11712   0.11101  -0.0103   1.0000   0.1800
  -9.000  -0.3625   0.11026   0.10413  -0.0071   1.0000   0.1918
  -8.750  -0.3885   0.10990   0.10394  -0.0111   1.0000   0.1961
  -8.500  -0.3600   0.10433   0.09839  -0.0087   1.0000   0.2096
  -8.250  -0.3505   0.10059   0.09473  -0.0084   1.0000   0.2204
  -8.000  -0.3747   0.09958   0.09390  -0.0114   1.0000   0.2282
  -7.750  -0.3642   0.09591   0.09032  -0.0104   1.0000   0.2438
  -7.500  -0.3594   0.09270   0.08722  -0.0098   1.0000   0.2597
  -7.250  -0.3589   0.08985   0.08450  -0.0092   1.0000   0.2760
  -7.000  -0.3351   0.08579   0.08051  -0.0067   1.0000   0.3009
  -6.750  -0.3424   0.08366   0.07855  -0.0057   1.0000   0.3231
  -6.500  -0.3281   0.08052   0.07553  -0.0033   1.0000   0.3532
  -6.250  -0.3222   0.07816   0.07332  -0.0006   1.0000   0.3866
  -6.000  -0.3036   0.07551   0.07080   0.0031   1.0000   0.4344
  -5.750  -0.2817   0.07321   0.06863   0.0080   1.0000   0.5007
  -5.500  -0.2076   0.06902   0.06442   0.0124   1.0000   0.6283
  -5.250  -0.0817   0.06137   0.05667   0.0066   1.0000   0.8150
  -4.500  -0.1314   0.05764   0.05339  -0.0035   0.9385   0.6820
  -4.250  -0.2071   0.05459   0.05040  -0.0126   0.9032   0.5681
  -4.000  -0.2049   0.04604   0.03969  -0.0463   0.8748   0.2229
  -3.750  -0.1659   0.04278   0.03536  -0.0475   0.8592   0.1593
  -3.500  -0.1363   0.04043   0.03241  -0.0470   0.8437   0.1429
  -3.250  -0.1083   0.03928   0.03036  -0.0454   0.8286   0.1315
  -3.000  -0.0796   0.03690   0.02780  -0.0451   0.8144   0.1285
  -2.750  -0.0489   0.03511   0.02564  -0.0445   0.8013   0.1246
  -2.500  -0.0186   0.03372   0.02387  -0.0438   0.7881   0.1230
  -2.250   0.0101   0.03276   0.02264  -0.0432   0.7745   0.1261
  -2.000   0.0424   0.03193   0.02150  -0.0431   0.7617   0.1323
  -1.750   0.2693   0.02429   0.01635  -0.0708   0.7448   1.0000
  -1.500   0.2895   0.02477   0.01641  -0.0697   0.7327   1.0000
  -1.250   0.3095   0.02519   0.01646  -0.0683   0.7226   1.0000
  -1.000   0.3289   0.02579   0.01682  -0.0675   0.7111   1.0000
  -0.750   0.3481   0.02647   0.01726  -0.0666   0.7008   1.0000
  -0.500   0.3681   0.02697   0.01750  -0.0652   0.6922   1.0000
  -0.250   0.3860   0.02790   0.01829  -0.0647   0.6821   1.0000
   0.000   0.4058   0.02847   0.01863  -0.0632   0.6744   1.0000
   0.250   0.4226   0.02953   0.01960  -0.0627   0.6649   1.0000
   0.500   0.4420   0.03024   0.02014  -0.0614   0.6581   1.0000
   0.750   0.4566   0.03152   0.02136  -0.0608   0.6493   1.0000
   1.000   0.4773   0.03211   0.02176  -0.0592   0.6432   1.0000
   1.250   0.4867   0.03391   0.02357  -0.0587   0.6347   1.0000
   1.500   0.5061   0.03470   0.02423  -0.0574   0.6288   1.0000
   1.750   0.5127   0.03666   0.02618  -0.0564   0.6215   1.0000
   2.000   0.5254   0.03803   0.02749  -0.0552   0.6151   1.0000
   2.250   0.5416   0.03921   0.02858  -0.0538   0.6099   1.0000
   2.500   0.5337   0.04212   0.03152  -0.0523   0.6037   1.0000
   2.750   0.5455   0.04360   0.03294  -0.0508   0.5983   1.0000
   3.000   0.5547   0.04535   0.03463  -0.0494   0.5935   1.0000
   3.250   0.5320   0.04897   0.03825  -0.0469   0.5905   1.0000
   3.500   0.5149   0.05203   0.04127  -0.0443   0.5882   1.0000
   3.750   0.4956   0.05488   0.04407  -0.0410   0.5876   1.0000
   4.000   0.4797   0.05763   0.04675  -0.0382   0.5889   1.0000
   4.250   0.4744   0.06025   0.04933  -0.0366   0.5915   1.0000
   4.500   0.4745   0.06292   0.05197  -0.0359   0.5965   1.0000
   4.750   0.3247   0.06975   0.05896  -0.0328   0.7585   1.0000
   5.000   0.3361   0.07139   0.06054  -0.0320   0.7454   1.0000
   5.250   0.3509   0.07330   0.06239  -0.0316   0.7324   1.0000
   5.500   0.3794   0.07630   0.06534  -0.0331   0.7226   1.0000
   5.750   0.3916   0.07786   0.06686  -0.0323   0.7091   1.0000
   6.000   0.3968   0.07923   0.06820  -0.0308   0.6962   1.0000
   6.250   0.4079   0.08117   0.07011  -0.0302   0.6846   1.0000
   6.500   0.4427   0.08487   0.07379  -0.0322   0.6753   1.0000
   6.750   0.4428   0.08571   0.07462  -0.0302   0.6619   1.0000
   7.000   0.4470   0.08732   0.07622  -0.0290   0.6504   1.0000
   7.250   0.4713   0.09054   0.07944  -0.0299   0.6421   1.0000
   7.750   0.4836   0.09381   0.08271  -0.0280   0.6174   1.0000
   8.000   0.5046   0.09701   0.08593  -0.0286   0.6096   1.0000
   8.250   0.5174   0.09904   0.08801  -0.0282   0.5970   1.0000
   8.500   0.5168   0.10058   0.08956  -0.0270   0.5855   1.0000
   8.750   0.5428   0.10444   0.09345  -0.0281   0.5783   1.0000
   9.000   0.5462   0.10587   0.09492  -0.0271   0.5656   1.0000
   9.250   0.5466   0.10768   0.09675  -0.0262   0.5548   1.0000
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