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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.2 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e598-il-1000000.txt
Download as CSV file: xf-e598-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 598 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3030   0.09340   0.09074  -0.0033   0.5988   0.0125
  -9.000  -0.3017   0.08854   0.08589  -0.0053   0.5950   0.0126
  -8.750  -0.3015   0.08411   0.08146  -0.0067   0.5906   0.0128
  -8.500  -0.2963   0.08094   0.07827  -0.0078   0.5857   0.0129
  -8.250  -0.2918   0.07758   0.07489  -0.0091   0.5814   0.0131
  -8.000  -0.2888   0.07395   0.07127  -0.0104   0.5776   0.0132
  -7.750  -0.4985   0.03014   0.02663  -0.0454   0.6062   0.0082
  -7.500  -0.4824   0.02642   0.02250  -0.0456   0.5999   0.0075
  -7.250  -0.4687   0.02200   0.01753  -0.0454   0.5947   0.0073
  -7.000  -0.4486   0.01939   0.01450  -0.0449   0.5886   0.0071
  -6.750  -0.4258   0.01756   0.01232  -0.0443   0.5824   0.0069
  -6.500  -0.4014   0.01616   0.01068  -0.0438   0.5774   0.0068
  -6.250  -0.3760   0.01507   0.00937  -0.0434   0.5719   0.0068
  -6.000  -0.3501   0.01420   0.00831  -0.0430   0.5662   0.0068
  -5.750  -0.3236   0.01344   0.00742  -0.0426   0.5616   0.0068
  -5.500  -0.2967   0.01279   0.00665  -0.0422   0.5565   0.0069
  -5.250  -0.2697   0.01223   0.00597  -0.0419   0.5518   0.0070
  -5.000  -0.2423   0.01175   0.00538  -0.0416   0.5474   0.0071
  -4.750  -0.2147   0.01129   0.00484  -0.0414   0.5431   0.0073
  -4.500  -0.1870   0.01091   0.00438  -0.0411   0.5386   0.0075
  -4.250  -0.1592   0.01056   0.00393  -0.0409   0.5343   0.0079
  -4.000  -0.1315   0.01013   0.00344  -0.0406   0.5307   0.0089
  -3.750  -0.1034   0.00979   0.00306  -0.0404   0.5268   0.0109
  -3.500  -0.0757   0.00941   0.00270  -0.0402   0.5227   0.0193
  -3.250  -0.0478   0.00919   0.00249  -0.0400   0.5188   0.0300
  -3.000  -0.0196   0.00904   0.00235  -0.0399   0.5152   0.0377
  -2.750   0.0088   0.00888   0.00222  -0.0398   0.5117   0.0451
  -2.500   0.0372   0.00876   0.00211  -0.0398   0.5080   0.0527
  -2.250   0.0655   0.00865   0.00201  -0.0397   0.5043   0.0620
  -2.000   0.0937   0.00859   0.00196  -0.0396   0.5002   0.0734
  -1.750   0.1223   0.00847   0.00188  -0.0396   0.4973   0.0836
  -1.500   0.1508   0.00838   0.00180  -0.0395   0.4939   0.0929
  -1.250   0.1794   0.00832   0.00173  -0.0395   0.4903   0.1018
  -1.000   0.2077   0.00825   0.00167  -0.0394   0.4865   0.1144
  -0.750   0.2361   0.00818   0.00162  -0.0394   0.4830   0.1276
  -0.500   0.2647   0.00809   0.00157  -0.0394   0.4799   0.1420
  -0.250   0.2932   0.00801   0.00153  -0.0393   0.4764   0.1601
   0.000   0.3215   0.00794   0.00150  -0.0393   0.4726   0.1842
   0.250   0.3495   0.00787   0.00150  -0.0393   0.4685   0.2216
   0.500   0.3777   0.00771   0.00150  -0.0393   0.4657   0.2767
   0.750   0.4053   0.00744   0.00150  -0.0392   0.4622   0.3714
   1.000   0.4263   0.00640   0.00153  -0.0381   0.4587   0.7487
   1.250   0.4737   0.00597   0.00161  -0.0418   0.4542   0.9881
   1.500   0.5270   0.00600   0.00159  -0.0472   0.4499   1.0000
   1.750   0.5540   0.00604   0.00160  -0.0469   0.4464   1.0000
   2.000   0.5809   0.00610   0.00162  -0.0465   0.4423   1.0000
   2.250   0.6077   0.00619   0.00165  -0.0462   0.4381   1.0000
   2.500   0.6347   0.00625   0.00169  -0.0459   0.4345   1.0000
   2.750   0.6618   0.00629   0.00172  -0.0456   0.4305   1.0000
   3.000   0.6887   0.00637   0.00177  -0.0454   0.4262   1.0000
   3.250   0.7155   0.00649   0.00183  -0.0451   0.4215   1.0000
   3.500   0.7427   0.00653   0.00188  -0.0449   0.4178   1.0000
   3.750   0.7698   0.00660   0.00194  -0.0446   0.4132   1.0000
   4.000   0.7966   0.00671   0.00202  -0.0444   0.4084   1.0000
   4.250   0.8236   0.00681   0.00210  -0.0442   0.4040   1.0000
   4.500   0.8507   0.00688   0.00217  -0.0440   0.3993   1.0000
   4.750   0.8776   0.00699   0.00227  -0.0437   0.3940   1.0000
   5.000   0.9044   0.00711   0.00237  -0.0435   0.3891   1.0000
   5.250   0.9315   0.00720   0.00246  -0.0434   0.3839   1.0000
   5.500   0.9582   0.00733   0.00258  -0.0432   0.3780   1.0000
   5.750   0.9851   0.00745   0.00270  -0.0430   0.3724   1.0000
   6.000   1.0120   0.00757   0.00281  -0.0428   0.3660   1.0000
   6.250   1.0386   0.00774   0.00296  -0.0427   0.3594   1.0000
   6.500   1.0655   0.00785   0.00309  -0.0425   0.3527   1.0000
   6.750   1.0919   0.00805   0.00326  -0.0424   0.3453   1.0000
   7.000   1.1188   0.00818   0.00341  -0.0423   0.3387   1.0000
   7.250   1.1450   0.00840   0.00360  -0.0421   0.3305   1.0000
   7.500   1.1717   0.00854   0.00376  -0.0420   0.3231   1.0000
   7.750   1.1978   0.00878   0.00398  -0.0418   0.3145   1.0000
   8.000   1.2240   0.00898   0.00418  -0.0417   0.3053   1.0000
   8.250   1.2499   0.00922   0.00441  -0.0416   0.2962   1.0000
   8.500   1.2753   0.00951   0.00468  -0.0414   0.2857   1.0000
   8.750   1.3009   0.00978   0.00494  -0.0412   0.2748   1.0000
   9.000   1.3259   0.01009   0.00523  -0.0410   0.2630   1.0000
   9.250   1.3505   0.01044   0.00555  -0.0407   0.2507   1.0000
   9.500   1.3744   0.01085   0.00592  -0.0404   0.2359   1.0000
   9.750   1.3976   0.01130   0.00633  -0.0401   0.2207   1.0000
  10.000   1.4203   0.01179   0.00677  -0.0396   0.2056   1.0000
  10.250   1.4419   0.01236   0.00727  -0.0391   0.1892   1.0000
  10.500   1.4621   0.01302   0.00785  -0.0384   0.1718   1.0000
  10.750   1.4814   0.01371   0.00847  -0.0377   0.1540   1.0000
  11.000   1.4988   0.01450   0.00917  -0.0367   0.1358   1.0000
  11.250   1.5144   0.01535   0.00994  -0.0355   0.1201   1.0000
  11.750   1.5399   0.01716   0.01165  -0.0326   0.0930   1.0000
  12.250   1.5467   0.01925   0.01370  -0.0272   0.0746   1.0000
  12.500   1.5435   0.02089   0.01532  -0.0249   0.0662   1.0000
  12.750   1.5420   0.02286   0.01730  -0.0237   0.0590   1.0000
  13.250   1.5433   0.02722   0.02172  -0.0225   0.0492   1.0000
  13.750   1.5423   0.03217   0.02675  -0.0219   0.0418   1.0000
  14.000   1.5395   0.03496   0.02957  -0.0217   0.0387   1.0000
  14.250   1.5377   0.03767   0.03233  -0.0215   0.0357   1.0000
  14.500   1.5319   0.04083   0.03552  -0.0215   0.0324   1.0000
  14.750   1.5293   0.04369   0.03844  -0.0215   0.0303   1.0000
  15.250   1.5191   0.05011   0.04496  -0.0219   0.0260   1.0000
  15.500   1.5143   0.05349   0.04840  -0.0223   0.0243   1.0000
  15.750   1.5100   0.05691   0.05187  -0.0228   0.0227   1.0000
  16.000   1.5067   0.06028   0.05531  -0.0234   0.0213   1.0000
  16.250   1.5017   0.06397   0.05905  -0.0241   0.0200   1.0000
  16.500   1.4985   0.06748   0.06263  -0.0249   0.0187   1.0000
  16.750   1.4940   0.07126   0.06647  -0.0258   0.0175   1.0000
  17.000   1.4880   0.07535   0.07062  -0.0270   0.0164   1.0000
  17.250   1.4849   0.07905   0.07439  -0.0280   0.0154   1.0000
  17.500   1.4802   0.08309   0.07850  -0.0292   0.0144   1.0000
  17.750   1.4739   0.08745   0.08293  -0.0307   0.0137   1.0000
  18.000   1.4687   0.09172   0.08728  -0.0321   0.0130   1.0000
  18.250   1.4653   0.09573   0.09136  -0.0335   0.0121   1.0000
  18.500   1.4592   0.10029   0.09599  -0.0353   0.0115   1.0000
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