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EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 552 AIRFOIL (e552-il)
Reynolds number: 200,000
Max Cl/Cd: 70.3 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e552-il-200000.txt
Download as CSV file: xf-e552-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 552 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.3325   0.11264   0.10930  -0.0509   1.0000   0.0349
 -13.750  -0.3289   0.11048   0.10718  -0.0508   1.0000   0.0341
 -13.500  -0.5854   0.08241   0.07827  -0.0685   1.0000   0.0291
 -13.250  -0.5731   0.07958   0.07550  -0.0677   1.0000   0.0281
 -13.000  -0.5930   0.07396   0.06978  -0.0704   1.0000   0.0278
 -12.750  -0.6112   0.06886   0.06457  -0.0725   1.0000   0.0273
 -12.500  -0.6322   0.06379   0.05935  -0.0742   1.0000   0.0268
 -12.250  -0.6532   0.05903   0.05440  -0.0754   1.0000   0.0262
 -12.000  -0.6809   0.05393   0.04903  -0.0760   1.0000   0.0253
 -11.750  -0.7304   0.04868   0.04317  -0.0751   1.0000   0.0240
 -11.500  -0.7447   0.04692   0.04122  -0.0730   1.0000   0.0237
 -11.250  -0.7574   0.04555   0.03973  -0.0698   1.0000   0.0236
 -11.000  -0.7615   0.04347   0.03753  -0.0670   1.0000   0.0235
 -10.750  -0.7632   0.04135   0.03532  -0.0643   1.0000   0.0234
 -10.250  -0.7344   0.03658   0.03015  -0.0646   0.9923   0.0234
 -10.000  -0.6974   0.03353   0.02689  -0.0672   0.9841   0.0238
  -9.750  -0.6589   0.03136   0.02473  -0.0691   0.9730   0.0247
  -9.500  -0.6195   0.02966   0.02300  -0.0715   0.9586   0.0258
  -9.250  -0.5755   0.02806   0.02132  -0.0746   0.9448   0.0277
  -9.000  -0.5279   0.02633   0.01957  -0.0788   0.9292   0.0302
  -8.750  -0.4765   0.02475   0.01786  -0.0852   0.9054   0.0352
  -8.500  -0.4408   0.02275   0.01584  -0.0897   0.8742   0.0405
  -8.250  -0.4283   0.02123   0.01418  -0.0900   0.8434   0.0465
  -8.000  -0.4189   0.02016   0.01298  -0.0887   0.8194   0.0547
  -7.750  -0.4105   0.01909   0.01184  -0.0870   0.8005   0.0669
  -7.500  -0.4008   0.01799   0.01074  -0.0854   0.7840   0.0887
  -7.250  -0.3926   0.01659   0.00956  -0.0839   0.7691   0.1342
  -7.000  -0.3865   0.01467   0.00824  -0.0826   0.7557   0.2482
  -6.750  -0.3702   0.01406   0.00824  -0.0815   0.7437   0.3980
  -6.500  -0.3434   0.01450   0.00851  -0.0810   0.7334   0.4361
  -6.250  -0.3166   0.01500   0.00889  -0.0804   0.7224   0.4570
  -6.000  -0.2892   0.01549   0.00925  -0.0799   0.7132   0.4718
  -5.750  -0.2618   0.01590   0.00953  -0.0794   0.7043   0.4839
  -5.500  -0.2348   0.01629   0.00975  -0.0790   0.6958   0.4963
  -5.250  -0.2065   0.01687   0.01034  -0.0782   0.6879   0.5052
  -5.000  -0.1795   0.01711   0.01046  -0.0779   0.6803   0.5143
  -4.750  -0.1516   0.01750   0.01079  -0.0773   0.6731   0.5212
  -4.500  -0.1242   0.01784   0.01103  -0.0769   0.6672   0.5309
  -4.250  -0.0968   0.01841   0.01163  -0.0760   0.6604   0.5395
  -4.000  -0.0695   0.01836   0.01140  -0.0761   0.6551   0.5462
  -3.750  -0.0421   0.01840   0.01140  -0.0759   0.6496   0.5493
  -3.500  -0.0148   0.01832   0.01125  -0.0759   0.6437   0.5527
  -3.250   0.0134   0.01814   0.01089  -0.0763   0.6389   0.5566
  -3.000   0.0412   0.01789   0.01046  -0.0770   0.6341   0.5608
  -2.750   0.0684   0.01776   0.01032  -0.0769   0.6291   0.5629
  -2.500   0.0965   0.01768   0.01016  -0.0771   0.6249   0.5651
  -2.250   0.1253   0.01766   0.01003  -0.0774   0.6214   0.5679
  -2.000   0.1526   0.01757   0.00992  -0.0776   0.6169   0.5710
  -1.750   0.1807   0.01744   0.00969  -0.0781   0.6124   0.5740
  -1.500   0.2097   0.01731   0.00941  -0.0787   0.6085   0.5772
  -1.250   0.2383   0.01730   0.00934  -0.0790   0.6054   0.5794
  -1.000   0.2654   0.01730   0.00938  -0.0790   0.6017   0.5819
  -0.750   0.2930   0.01730   0.00937  -0.0792   0.5980   0.5844
  -0.500   0.3214   0.01728   0.00930  -0.0796   0.5945   0.5873
  -0.250   0.3507   0.01726   0.00918  -0.0801   0.5913   0.5905
   0.000   0.3802   0.01732   0.00912  -0.0807   0.5884   0.5939
   0.250   0.4063   0.01735   0.00925  -0.0806   0.5849   0.5964
   0.500   0.4337   0.01742   0.00936  -0.0807   0.5815   0.5991
   0.750   0.4618   0.01747   0.00940  -0.0810   0.5784   0.6021
   1.000   0.4910   0.01752   0.00939  -0.0815   0.5755   0.6056
   1.250   0.5212   0.01766   0.00940  -0.0822   0.5730   0.6093
   1.500   0.5467   0.01775   0.00963  -0.0820   0.5697   0.6121
   1.750   0.5731   0.01789   0.00985  -0.0820   0.5664   0.6154
   2.000   0.6007   0.01800   0.00998  -0.0822   0.5632   0.6192
   2.250   0.6296   0.01809   0.01004  -0.0826   0.5603   0.6233
   2.500   0.6591   0.01823   0.01014  -0.0831   0.5580   0.6271
   2.750   0.6851   0.01843   0.01044  -0.0830   0.5550   0.6303
   3.000   0.7105   0.01863   0.01075  -0.0828   0.5514   0.6343
   3.250   0.7377   0.01881   0.01096  -0.0830   0.5481   0.6393
   3.500   0.7658   0.01892   0.01110  -0.0833   0.5452   0.6439
   3.750   0.7945   0.01905   0.01126  -0.0835   0.5426   0.6483
   4.000   0.8211   0.01933   0.01159  -0.0836   0.5395   0.6535
   4.250   0.8456   0.01958   0.01195  -0.0834   0.5354   0.6589
   4.500   0.8715   0.01973   0.01221  -0.0832   0.5317   0.6635
   4.750   0.9000   0.01982   0.01233  -0.0834   0.5285   0.6694
   5.000   0.9303   0.01996   0.01243  -0.0840   0.5257   0.6759
   5.250   0.9516   0.02026   0.01296  -0.0831   0.5212   0.6818
   5.500   0.9769   0.02047   0.01325  -0.0830   0.5168   0.6896
   5.750   1.0046   0.02050   0.01336  -0.0830   0.5132   0.6962
   6.000   1.0355   0.02057   0.01341  -0.0836   0.5101   0.7047
   6.250   1.0556   0.02087   0.01393  -0.0825   0.5049   0.7121
   6.500   1.0809   0.02096   0.01412  -0.0822   0.4999   0.7219
   6.750   1.1101   0.02084   0.01406  -0.0824   0.4959   0.7312
   7.000   1.1350   0.02100   0.01432  -0.0820   0.4912   0.7423
   7.250   1.1564   0.02114   0.01464  -0.0811   0.4853   0.7549
   7.500   1.1842   0.02099   0.01457  -0.0809   0.4808   0.7680
   7.750   1.2092   0.02100   0.01469  -0.0804   0.4757   0.7825
   8.000   1.2284   0.02104   0.01493  -0.0790   0.4691   0.7993
   8.250   1.2562   0.02074   0.01468  -0.0787   0.4640   0.8195
   8.500   1.2721   0.02078   0.01496  -0.0765   0.4574   0.8447
   8.750   1.2897   0.02050   0.01485  -0.0744   0.4510   0.8827
   9.000   1.3148   0.02016   0.01464  -0.0737   0.4445   1.0000
   9.250   1.3377   0.02020   0.01477  -0.0733   0.4362   1.0000
   9.500   1.3623   0.02016   0.01474  -0.0730   0.4284   1.0000
   9.750   1.3825   0.02013   0.01478  -0.0719   0.4192   1.0000
  10.000   1.3990   0.02023   0.01497  -0.0702   0.4092   1.0000
  10.250   1.4168   0.02023   0.01499  -0.0686   0.3989   1.0000
  10.500   1.4299   0.02034   0.01515  -0.0664   0.3868   1.0000
  10.750   1.4361   0.02063   0.01552  -0.0631   0.3734   1.0000
  11.000   1.4403   0.02106   0.01598  -0.0596   0.3589   1.0000
  11.250   1.4424   0.02170   0.01660  -0.0562   0.3431   1.0000
  11.500   1.4411   0.02264   0.01751  -0.0527   0.3258   1.0000
  11.750   1.4371   0.02393   0.01877  -0.0494   0.3077   1.0000
  12.000   1.4307   0.02561   0.02039  -0.0464   0.2901   1.0000
  12.250   1.4219   0.02769   0.02241  -0.0438   0.2729   1.0000
  12.500   1.4124   0.03011   0.02477  -0.0417   0.2568   1.0000
  12.750   1.4021   0.03283   0.02744  -0.0400   0.2413   1.0000
  13.000   1.3922   0.03574   0.03032  -0.0386   0.2267   1.0000
  13.250   1.3824   0.03882   0.03337  -0.0376   0.2129   1.0000
  13.500   1.3728   0.04203   0.03657  -0.0368   0.1997   1.0000
  13.750   1.3640   0.04529   0.03981  -0.0363   0.1874   1.0000
  14.000   1.3551   0.04870   0.04320  -0.0359   0.1756   1.0000
  14.250   1.3462   0.05223   0.04668  -0.0357   0.1648   1.0000
  14.500   1.3391   0.05575   0.05019  -0.0357   0.1537   1.0000
  14.750   1.3336   0.05921   0.05367  -0.0359   0.1432   1.0000
  15.000   1.3277   0.06281   0.05725  -0.0362   0.1334   1.0000
  15.250   1.3206   0.06660   0.06098  -0.0366   0.1247   1.0000
  15.500   1.3174   0.07013   0.06457  -0.0372   0.1153   1.0000
  15.750   1.3129   0.07386   0.06829  -0.0378   0.1070   1.0000
  16.000   1.3073   0.07775   0.07213  -0.0386   0.0996   1.0000
  16.250   1.3051   0.08138   0.07584  -0.0394   0.0919   1.0000
  16.500   1.3001   0.08530   0.07967  -0.0402   0.0856   1.0000
  16.750   1.2986   0.08900   0.08351  -0.0412   0.0792   1.0000
  17.000   1.2945   0.09290   0.08733  -0.0422   0.0736   1.0000
  17.250   1.2932   0.09669   0.09125  -0.0434   0.0683   1.0000
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