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EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 554 AIRFOIL (e554-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.84 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e554-il-1000000.txt
Download as CSV file: xf-e554-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.7390   0.13829   0.13585  -0.0247   1.0000   0.0050
 -18.750  -0.7574   0.13019   0.12763  -0.0288   1.0000   0.0049
 -18.500  -0.7769   0.12215   0.11947  -0.0328   1.0000   0.0049
 -18.250  -0.7964   0.11435   0.11153  -0.0367   1.0000   0.0050
 -18.000  -0.8080   0.10829   0.10537  -0.0397   1.0000   0.0049
 -17.750  -0.8194   0.10242   0.09939  -0.0426   1.0000   0.0049
 -17.500  -0.8317   0.09660   0.09346  -0.0453   1.0000   0.0048
 -17.250  -0.8418   0.09108   0.08783  -0.0480   1.0000   0.0051
 -17.000  -0.8496   0.08646   0.08313  -0.0499   1.0000   0.0048
 -16.750  -0.8556   0.08188   0.07844  -0.0520   1.0000   0.0051
 -16.500  -0.8641   0.07733   0.07380  -0.0538   1.0000   0.0049
 -16.250  -0.8680   0.07341   0.06978  -0.0555   1.0000   0.0050
 -16.000  -0.8717   0.06963   0.06592  -0.0569   1.0000   0.0050
 -15.750  -0.8744   0.06608   0.06227  -0.0582   1.0000   0.0051
 -15.500  -0.8755   0.06287   0.05900  -0.0592   1.0000   0.0051
 -15.250  -0.8754   0.05978   0.05582  -0.0603   1.0000   0.0052
 -15.000  -0.8734   0.05705   0.05303  -0.0611   1.0000   0.0052
 -14.750  -0.8759   0.05399   0.04989  -0.0618   1.0000   0.0052
 -14.500  -0.8695   0.05181   0.04764  -0.0624   1.0000   0.0053
 -14.250  -0.8824   0.04797   0.04369  -0.0628   1.0000   0.0055
 -14.000  -0.8790   0.04578   0.04145  -0.0630   1.0000   0.0055
 -13.750  -0.8851   0.04287   0.03848  -0.0631   1.0000   0.0056
 -13.500  -0.8872   0.04043   0.03598  -0.0631   1.0000   0.0057
 -13.250  -0.8853   0.03842   0.03392  -0.0628   1.0000   0.0058
 -13.000  -0.8834   0.03646   0.03192  -0.0625   1.0000   0.0058
 -12.750  -0.8829   0.03448   0.02989  -0.0619   1.0000   0.0059
 -12.500  -0.8824   0.03258   0.02795  -0.0612   1.0000   0.0060
 -12.250  -0.8804   0.03088   0.02621  -0.0603   1.0000   0.0061
 -12.000  -0.8814   0.02907   0.02436  -0.0592   1.0000   0.0061
 -11.750  -0.8816   0.02749   0.02275  -0.0578   1.0000   0.0063
 -11.500  -0.8658   0.02592   0.02114  -0.0591   0.9989   0.0065
 -11.250  -0.8358   0.02403   0.01919  -0.0637   0.9953   0.0066
 -11.000  -0.8091   0.02235   0.01744  -0.0672   0.9896   0.0068
 -10.750  -0.7951   0.02080   0.01583  -0.0681   0.9716   0.0070
 -10.500  -0.7657   0.01929   0.01425  -0.0716   0.9517   0.0071
 -10.250  -0.7111   0.01709   0.01193  -0.0812   0.9360   0.0076
 -10.000  -0.6342   0.01581   0.01057  -0.0932   0.9163   0.0085
  -9.750  -0.5893   0.01514   0.00964  -0.0981   0.8642   0.0091
  -9.500  -0.5748   0.01466   0.00895  -0.0966   0.8244   0.0096
  -9.250  -0.5592   0.01418   0.00833  -0.0952   0.7952   0.0103
  -9.000  -0.5402   0.01381   0.00784  -0.0941   0.7725   0.0113
  -8.250  -0.4771   0.01263   0.00642  -0.0920   0.7196   0.0176
  -8.000  -0.4542   0.01224   0.00600  -0.0916   0.7047   0.0226
  -7.750  -0.4306   0.01187   0.00561  -0.0912   0.6906   0.0294
  -7.500  -0.4064   0.01154   0.00525  -0.0909   0.6770   0.0374
  -7.250  -0.3821   0.01118   0.00489  -0.0907   0.6637   0.0492
  -7.000  -0.3571   0.01077   0.00453  -0.0906   0.6520   0.0673
  -6.750  -0.3322   0.01030   0.00414  -0.0906   0.6413   0.0935
  -6.500  -0.3071   0.00983   0.00377  -0.0906   0.6305   0.1283
  -6.250  -0.2819   0.00917   0.00332  -0.0907   0.6209   0.1824
  -6.000  -0.2579   0.00829   0.00277  -0.0910   0.6111   0.2745
  -5.750  -0.2309   0.00779   0.00251  -0.0913   0.6022   0.3450
  -5.500  -0.2030   0.00768   0.00243  -0.0914   0.5929   0.3755
  -5.250  -0.1742   0.00764   0.00237  -0.0916   0.5842   0.3896
  -5.000  -0.1456   0.00766   0.00231  -0.0917   0.5755   0.3979
  -4.750  -0.1166   0.00764   0.00227  -0.0919   0.5678   0.4055
  -4.500  -0.0879   0.00770   0.00224  -0.0920   0.5600   0.4136
  -4.250  -0.0589   0.00768   0.00222  -0.0922   0.5534   0.4211
  -4.000  -0.0299   0.00773   0.00219  -0.0923   0.5464   0.4261
  -3.750  -0.0011   0.00776   0.00217  -0.0925   0.5398   0.4325
  -3.500   0.0281   0.00782   0.00222  -0.0927   0.5336   0.4408
  -3.250   0.0569   0.00791   0.00222  -0.0928   0.5271   0.4449
  -3.000   0.0858   0.00789   0.00217  -0.0930   0.5216   0.4476
  -2.750   0.1148   0.00786   0.00212  -0.0932   0.5164   0.4506
  -2.500   0.1436   0.00788   0.00210  -0.0933   0.5111   0.4530
  -2.250   0.1723   0.00792   0.00210  -0.0935   0.5062   0.4555
  -2.000   0.2016   0.00793   0.00208  -0.0937   0.5020   0.4580
  -1.750   0.2306   0.00796   0.00207  -0.0939   0.4974   0.4603
  -1.500   0.2593   0.00802   0.00207  -0.0941   0.4925   0.4621
  -1.250   0.2881   0.00802   0.00205  -0.0942   0.4885   0.4647
  -1.000   0.3172   0.00800   0.00205  -0.0945   0.4851   0.4678
  -0.750   0.3461   0.00802   0.00206  -0.0947   0.4814   0.4706
  -0.500   0.3748   0.00807   0.00208  -0.0948   0.4776   0.4731
  -0.250   0.4031   0.00816   0.00211  -0.0949   0.4731   0.4755
   0.000   0.4324   0.00817   0.00213  -0.0952   0.4705   0.4778
   0.250   0.4615   0.00821   0.00215  -0.0954   0.4675   0.4797
   0.500   0.4903   0.00821   0.00216  -0.0956   0.4643   0.4830
   0.750   0.5188   0.00825   0.00220  -0.0957   0.4610   0.4862
   1.000   0.5469   0.00834   0.00226  -0.0958   0.4570   0.4891
   1.250   0.5758   0.00837   0.00231  -0.0960   0.4546   0.4918
   1.500   0.6048   0.00841   0.00236  -0.0962   0.4522   0.4944
   1.750   0.6336   0.00846   0.00240  -0.0964   0.4493   0.4967
   2.000   0.6621   0.00849   0.00244  -0.0965   0.4464   0.4997
   2.250   0.6903   0.00855   0.00251  -0.0966   0.4433   0.5031
   2.500   0.7180   0.00867   0.00262  -0.0967   0.4396   0.5063
   2.750   0.7469   0.00870   0.00268  -0.0969   0.4377   0.5097
   3.000   0.7757   0.00874   0.00275  -0.0971   0.4353   0.5128
   3.250   0.8042   0.00880   0.00281  -0.0972   0.4326   0.5153
   3.500   0.8324   0.00884   0.00289  -0.0973   0.4297   0.5195
   3.750   0.8603   0.00892   0.00298  -0.0974   0.4267   0.5231
   4.000   0.8876   0.00907   0.00311  -0.0974   0.4229   0.5268
   4.250   0.9162   0.00910   0.00319  -0.0975   0.4208   0.5303
   4.500   0.9446   0.00914   0.00327  -0.0977   0.4178   0.5336
   4.750   0.9727   0.00918   0.00336  -0.0978   0.4144   0.5385
   5.000   1.0002   0.00927   0.00346  -0.0978   0.4106   0.5431
   5.250   1.0269   0.00943   0.00361  -0.0977   0.4064   0.5475
   5.500   1.0553   0.00946   0.00370  -0.0978   0.4038   0.5516
   5.750   1.0833   0.00950   0.00381  -0.0979   0.4005   0.5569
   6.000   1.1107   0.00957   0.00392  -0.0979   0.3965   0.5622
   6.250   1.1371   0.00972   0.00406  -0.0977   0.3917   0.5673
   6.500   1.1646   0.00979   0.00419  -0.0977   0.3879   0.5733
   6.750   1.1922   0.00984   0.00431  -0.0978   0.3836   0.5799
   7.000   1.2188   0.00996   0.00445  -0.0977   0.3787   0.5862
   7.250   1.2447   0.01010   0.00462  -0.0974   0.3734   0.5935
   7.500   1.2721   0.01016   0.00476  -0.0974   0.3681   0.6011
   7.750   1.2979   0.01029   0.00492  -0.0972   0.3612   0.6088
   8.000   1.3239   0.01042   0.00509  -0.0970   0.3548   0.6178
   8.250   1.3493   0.01057   0.00528  -0.0967   0.3464   0.6271
   8.500   1.3743   0.01075   0.00548  -0.0963   0.3375   0.6377
   8.750   1.3977   0.01098   0.00573  -0.0957   0.3261   0.6486
   9.000   1.4203   0.01127   0.00601  -0.0949   0.3122   0.6599
   9.250   1.4412   0.01162   0.00634  -0.0939   0.2948   0.6726
   9.500   1.4608   0.01203   0.00672  -0.0927   0.2767   0.6863
   9.750   1.4782   0.01252   0.00718  -0.0911   0.2571   0.7016
  10.000   1.4918   0.01316   0.00774  -0.0890   0.2351   0.7189
  10.250   1.5024   0.01376   0.00830  -0.0863   0.2135   0.7384
  10.750   1.5157   0.01512   0.00962  -0.0796   0.1773   0.7894
  11.000   1.5209   0.01581   0.01035  -0.0761   0.1623   0.8301
  11.250   1.5223   0.01621   0.01098  -0.0718   0.1511   1.0000
  11.500   1.5268   0.01712   0.01184  -0.0688   0.1382   1.0000
  11.750   1.5308   0.01811   0.01280  -0.0659   0.1271   1.0000
  12.000   1.5327   0.01927   0.01393  -0.0630   0.1167   1.0000
  12.250   1.5330   0.02062   0.01526  -0.0602   0.1074   1.0000
  12.500   1.5342   0.02208   0.01670  -0.0579   0.0990   1.0000
  12.750   1.5339   0.02377   0.01840  -0.0558   0.0909   1.0000
  13.000   1.5318   0.02576   0.02039  -0.0539   0.0839   1.0000
  13.250   1.5301   0.02789   0.02252  -0.0524   0.0770   1.0000
  13.500   1.5286   0.03016   0.02482  -0.0512   0.0713   1.0000
  13.750   1.5233   0.03289   0.02755  -0.0501   0.0651   1.0000
  14.000   1.5217   0.03543   0.03013  -0.0493   0.0604   1.0000
  14.250   1.5157   0.03848   0.03319  -0.0487   0.0555   1.0000
  14.500   1.5106   0.04155   0.03629  -0.0482   0.0508   1.0000
  14.750   1.5059   0.04469   0.03946  -0.0480   0.0471   1.0000
  15.000   1.5016   0.04788   0.04270  -0.0478   0.0437   1.0000
  15.250   1.4956   0.05136   0.04621  -0.0479   0.0398   1.0000
  15.500   1.4919   0.05471   0.04960  -0.0481   0.0373   1.0000
  15.750   1.4876   0.05821   0.05315  -0.0485   0.0347   1.0000
  16.000   1.4840   0.06173   0.05671  -0.0489   0.0322   1.0000
  16.250   1.4794   0.06546   0.06049  -0.0495   0.0297   1.0000
  16.500   1.4771   0.06897   0.06404  -0.0502   0.0277   1.0000
  16.750   1.4734   0.07273   0.06785  -0.0510   0.0258   1.0000
  17.000   1.4707   0.07647   0.07163  -0.0519   0.0239   1.0000
  17.250   1.4665   0.08046   0.07567  -0.0530   0.0220   1.0000
  17.500   1.4654   0.08407   0.07933  -0.0540   0.0206   1.0000
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