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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 200,000
Max Cl/Cd: 68.98 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e554-il-200000.txt
Download as CSV file: xf-e554-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 554 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.5175   0.11353   0.10966  -0.0477   1.0000   0.0282
 -14.500  -0.5271   0.10718   0.10329  -0.0506   1.0000   0.0280
 -14.250  -0.6387   0.08352   0.07903  -0.0661   1.0000   0.0241
 -14.000  -0.6425   0.07944   0.07492  -0.0673   1.0000   0.0239
 -13.750  -0.6616   0.07407   0.06941  -0.0700   1.0000   0.0238
 -13.500  -0.6771   0.06925   0.06446  -0.0719   1.0000   0.0237
 -13.250  -0.6935   0.06479   0.05984  -0.0736   1.0000   0.0237
 -13.000  -0.7047   0.06097   0.05588  -0.0747   1.0000   0.0236
 -12.750  -0.7182   0.05708   0.05183  -0.0755   1.0000   0.0235
 -12.500  -0.7313   0.05356   0.04812  -0.0759   1.0000   0.0235
 -12.250  -0.7401   0.05057   0.04495  -0.0758   1.0000   0.0235
 -12.000  -0.7488   0.04768   0.04188  -0.0752   1.0000   0.0235
 -11.750  -0.7588   0.04512   0.03911  -0.0741   1.0000   0.0237
 -11.500  -0.7677   0.04297   0.03678  -0.0724   1.0000   0.0238
 -11.250  -0.7692   0.04105   0.03471  -0.0704   1.0000   0.0238
 -11.000  -0.7751   0.03939   0.03291  -0.0676   1.0000   0.0239
 -10.750  -0.7800   0.03784   0.03119  -0.0645   1.0000   0.0241
 -10.500  -0.7720   0.03611   0.02936  -0.0623   1.0000   0.0242
 -10.250  -0.7560   0.03460   0.02789  -0.0604   1.0000   0.0247
 -10.000  -0.7537   0.03358   0.02690  -0.0574   1.0000   0.0252
  -9.750  -0.7472   0.03260   0.02592  -0.0553   0.9989   0.0257
  -9.500  -0.7060   0.03104   0.02428  -0.0582   0.9940   0.0270
  -9.250  -0.6678   0.02951   0.02267  -0.0603   0.9872   0.0286
  -9.000  -0.6314   0.02799   0.02124  -0.0635   0.9766   0.0312
  -8.750  -0.5982   0.02631   0.01958  -0.0665   0.9629   0.0343
  -8.500  -0.5652   0.02453   0.01778  -0.0697   0.9484   0.0386
  -8.250  -0.5321   0.02249   0.01576  -0.0736   0.9337   0.0448
  -8.000  -0.4931   0.02049   0.01379  -0.0788   0.9191   0.0571
  -7.750  -0.4552   0.01829   0.01170  -0.0840   0.9013   0.0817
  -7.500  -0.4224   0.01595   0.00969  -0.0885   0.8803   0.1460
  -7.250  -0.4006   0.01359   0.00825  -0.0910   0.8575   0.3212
  -7.000  -0.3700   0.01375   0.00842  -0.0915   0.8363   0.3884
  -6.750  -0.3403   0.01413   0.00858  -0.0915   0.8164   0.4149
  -6.500  -0.3118   0.01457   0.00884  -0.0912   0.7980   0.4317
  -6.250  -0.2841   0.01496   0.00899  -0.0909   0.7811   0.4456
  -6.000  -0.2560   0.01553   0.00952  -0.0901   0.7659   0.4555
  -5.750  -0.2284   0.01593   0.00975  -0.0896   0.7521   0.4663
  -5.500  -0.2014   0.01639   0.01013  -0.0888   0.7379   0.4754
  -5.250  -0.1746   0.01660   0.01021  -0.0883   0.7248   0.4832
  -5.000  -0.1471   0.01705   0.01059  -0.0876   0.7131   0.4903
  -4.750  -0.1204   0.01732   0.01071  -0.0871   0.7016   0.4998
  -4.500  -0.0935   0.01783   0.01123  -0.0861   0.6904   0.5062
  -4.250  -0.0658   0.01779   0.01096  -0.0862   0.6813   0.5128
  -4.000  -0.0392   0.01754   0.01060  -0.0863   0.6711   0.5169
  -3.750  -0.0115   0.01754   0.01049  -0.0861   0.6631   0.5197
  -3.500   0.0154   0.01746   0.01035  -0.0860   0.6537   0.5229
  -3.250   0.0436   0.01737   0.01008  -0.0862   0.6464   0.5266
  -3.000   0.0711   0.01715   0.00973  -0.0866   0.6377   0.5311
  -2.750   0.0993   0.01695   0.00938  -0.0869   0.6308   0.5341
  -2.500   0.1267   0.01689   0.00929  -0.0869   0.6239   0.5366
  -2.250   0.1543   0.01686   0.00921  -0.0868   0.6172   0.5397
  -2.000   0.1831   0.01684   0.00905  -0.0871   0.6117   0.5430
  -1.750   0.2108   0.01673   0.00889  -0.0874   0.6050   0.5465
  -1.500   0.2398   0.01663   0.00863  -0.0880   0.5989   0.5505
  -1.250   0.2682   0.01660   0.00853  -0.0881   0.5941   0.5532
  -1.000   0.2953   0.01659   0.00856  -0.0881   0.5885   0.5560
  -0.750   0.3233   0.01658   0.00853  -0.0882   0.5833   0.5592
  -0.500   0.3523   0.01659   0.00843  -0.0886   0.5788   0.5627
  -0.250   0.3812   0.01662   0.00837  -0.0891   0.5742   0.5666
   0.000   0.4088   0.01658   0.00834  -0.0892   0.5689   0.5700
   0.250   0.4366   0.01661   0.00838  -0.0892   0.5645   0.5731
   0.500   0.4655   0.01669   0.00841  -0.0895   0.5608   0.5766
   0.750   0.4938   0.01679   0.00849  -0.0898   0.5569   0.5803
   1.000   0.5216   0.01684   0.00853  -0.0900   0.5522   0.5844
   1.250   0.5498   0.01686   0.00854  -0.0903   0.5479   0.5879
   1.500   0.5781   0.01694   0.00863  -0.0904   0.5444   0.5913
   1.750   0.6071   0.01713   0.00879  -0.0907   0.5412   0.5955
   2.000   0.6336   0.01723   0.00896  -0.0907   0.5369   0.6002
   2.250   0.6616   0.01733   0.00906  -0.0910   0.5327   0.6046
   2.500   0.6893   0.01740   0.00918  -0.0910   0.5291   0.6080
   2.750   0.7183   0.01756   0.00931  -0.0913   0.5260   0.6122
   3.000   0.7459   0.01777   0.00956  -0.0915   0.5225   0.6171
   3.250   0.7724   0.01792   0.00978  -0.0915   0.5183   0.6224
   3.500   0.7989   0.01805   0.01001  -0.0914   0.5145   0.6267
   3.750   0.8271   0.01819   0.01018  -0.0915   0.5111   0.6319
   4.000   0.8572   0.01841   0.01032  -0.0921   0.5080   0.6377
   4.250   0.8824   0.01862   0.01068  -0.0919   0.5043   0.6425
   4.500   0.9075   0.01882   0.01101  -0.0915   0.5001   0.6478
   4.750   0.9348   0.01899   0.01123  -0.0916   0.4962   0.6546
   5.000   0.9632   0.01913   0.01140  -0.0918   0.4929   0.6606
   5.250   0.9918   0.01941   0.01169  -0.0921   0.4896   0.6674
   5.500   1.0151   0.01966   0.01210  -0.0915   0.4850   0.6748
   5.750   1.0400   0.01981   0.01240  -0.0911   0.4805   0.6811
   6.000   1.0683   0.01992   0.01254  -0.0913   0.4766   0.6897
   6.250   1.0978   0.02013   0.01274  -0.0917   0.4730   0.6977
   6.500   1.1185   0.02037   0.01321  -0.0906   0.4676   0.7073
   6.750   1.1431   0.02046   0.01343  -0.0901   0.4626   0.7163
   7.000   1.1723   0.02052   0.01349  -0.0904   0.4584   0.7275
   7.250   1.1961   0.02074   0.01386  -0.0898   0.4537   0.7383
   7.500   1.2172   0.02089   0.01421  -0.0887   0.4479   0.7506
   7.750   1.2437   0.02087   0.01425  -0.0885   0.4430   0.7651
   8.000   1.2696   0.02097   0.01442  -0.0881   0.4380   0.7813
   8.250   1.2870   0.02107   0.01477  -0.0864   0.4314   0.7993
   8.500   1.3112   0.02094   0.01473  -0.0855   0.4259   0.8211
   8.750   1.3309   0.02098   0.01492  -0.0840   0.4202   0.8495
   9.000   1.3415   0.02087   0.01507  -0.0806   0.4137   0.9000
   9.250   1.3714   0.02063   0.01481  -0.0810   0.4074   1.0000
   9.500   1.3902   0.02088   0.01521  -0.0800   0.3992   1.0000
   9.750   1.4157   0.02084   0.01514  -0.0797   0.3918   1.0000
  10.000   1.4322   0.02107   0.01550  -0.0781   0.3831   1.0000
  10.250   1.4540   0.02108   0.01547  -0.0772   0.3749   1.0000
  10.500   1.4655   0.02135   0.01592  -0.0748   0.3649   1.0000
  10.750   1.4801   0.02153   0.01612  -0.0728   0.3552   1.0000
  11.000   1.4883   0.02179   0.01642  -0.0698   0.3444   1.0000
  11.250   1.4932   0.02223   0.01696  -0.0664   0.3325   1.0000
  11.500   1.4973   0.02281   0.01757  -0.0632   0.3199   1.0000
  11.750   1.4991   0.02359   0.01836  -0.0599   0.3064   1.0000
  12.000   1.4983   0.02464   0.01941  -0.0568   0.2921   1.0000
  12.250   1.4949   0.02603   0.02078  -0.0538   0.2772   1.0000
  12.500   1.4890   0.02778   0.02252  -0.0511   0.2621   1.0000
  12.750   1.4812   0.02992   0.02463  -0.0488   0.2473   1.0000
  13.000   1.4717   0.03246   0.02715  -0.0468   0.2328   1.0000
  13.250   1.4610   0.03535   0.03000  -0.0453   0.2192   1.0000
  13.500   1.4491   0.03858   0.03320  -0.0442   0.2059   1.0000
  13.750   1.4382   0.04196   0.03659  -0.0435   0.1932   1.0000
  14.000   1.4271   0.04553   0.04017  -0.0431   0.1813   1.0000
  14.250   1.4158   0.04928   0.04392  -0.0429   0.1702   1.0000
  14.500   1.4036   0.05327   0.04787  -0.0429   0.1602   1.0000
  14.750   1.3936   0.05724   0.05185  -0.0432   0.1498   1.0000
  15.000   1.3851   0.06119   0.05583  -0.0436   0.1401   1.0000
  15.250   1.3755   0.06536   0.05997  -0.0442   0.1313   1.0000
  15.500   1.3671   0.06955   0.06416  -0.0450   0.1227   1.0000
  15.750   1.3608   0.07361   0.06826  -0.0458   0.1143   1.0000
  16.000   1.3524   0.07795   0.07254  -0.0468   0.1072   1.0000
  16.250   1.3473   0.08206   0.07672  -0.0479   0.0995   1.0000
  16.500   1.3416   0.08624   0.08089  -0.0490   0.0929   1.0000
  16.750   1.3363   0.09050   0.08517  -0.0502   0.0867   1.0000
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