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EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 598 AIRFOIL (e598-il)
Reynolds number: 200,000
Max Cl/Cd: 72.17 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e598-il-200000.txt
Download as CSV file: xf-e598-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3249   0.10706   0.10364  -0.0081   0.8022   0.0404
  -9.000  -0.3299   0.10418   0.10069  -0.0116   0.7849   0.0414
  -8.750  -0.3372   0.10089   0.09737  -0.0160   0.7710   0.0417
  -8.500  -0.3248   0.09694   0.09335  -0.0150   0.7578   0.0422
  -8.250  -0.3116   0.09410   0.09042  -0.0142   0.7459   0.0430
  -8.000  -0.3036   0.09132   0.08759  -0.0148   0.7349   0.0440
  -7.750  -0.2986   0.08835   0.08459  -0.0161   0.7253   0.0449
  -7.500  -0.2963   0.08529   0.08150  -0.0178   0.7171   0.0463
  -7.250  -0.3040   0.08197   0.07821  -0.0216   0.7090   0.0479
  -7.000  -0.3121   0.07642   0.07260  -0.0333   0.7031   0.0486
  -6.750  -0.3021   0.07296   0.06913  -0.0314   0.6962   0.0492
  -6.500  -0.2895   0.07032   0.06647  -0.0307   0.6886   0.0499
  -6.250  -0.2777   0.06749   0.06356  -0.0316   0.6827   0.0511
  -6.000  -0.2649   0.06391   0.05994  -0.0344   0.6759   0.0526
  -5.750  -0.2782   0.03501   0.02968  -0.0493   0.6786   0.0263
  -5.500  -0.2595   0.03120   0.02550  -0.0494   0.6721   0.0257
  -5.250  -0.2405   0.02683   0.02040  -0.0490   0.6669   0.0254
  -5.000  -0.2176   0.02356   0.01642  -0.0484   0.6609   0.0257
  -4.750  -0.1927   0.02162   0.01410  -0.0479   0.6548   0.0271
  -4.500  -0.1666   0.02077   0.01298  -0.0475   0.6496   0.0298
  -4.250  -0.1398   0.01989   0.01201  -0.0473   0.6433   0.0336
  -4.000  -0.1129   0.01869   0.01059  -0.0467   0.6375   0.0378
  -3.750  -0.0860   0.01809   0.00984  -0.0463   0.6328   0.0454
  -3.500  -0.0580   0.01768   0.00932  -0.0460   0.6270   0.0568
  -3.250  -0.0309   0.01727   0.00894  -0.0459   0.6214   0.0686
  -3.000  -0.0036   0.01702   0.00861  -0.0455   0.6168   0.0804
  -2.750   0.0241   0.01668   0.00822  -0.0454   0.6116   0.0919
  -2.500   0.0520   0.01637   0.00784  -0.0452   0.6063   0.1033
  -2.250   0.0795   0.01613   0.00753  -0.0449   0.6017   0.1150
  -2.000   0.1067   0.01579   0.00718  -0.0446   0.5973   0.1275
  -1.750   0.1344   0.01545   0.00689  -0.0445   0.5919   0.1411
  -1.500   0.1618   0.01516   0.00659  -0.0442   0.5873   0.1562
  -1.250   0.1889   0.01493   0.00632  -0.0439   0.5833   0.1737
  -1.000   0.2163   0.01473   0.00619  -0.0437   0.5783   0.1952
  -0.750   0.2434   0.01446   0.00605  -0.0436   0.5733   0.2231
  -0.500   0.2700   0.01416   0.00589  -0.0432   0.5692   0.2689
  -0.250   0.2934   0.01347   0.00578  -0.0426   0.5656   0.4271
   0.000   0.3655   0.01205   0.00574  -0.0507   0.5588   1.0000
   0.250   0.3918   0.01218   0.00570  -0.0503   0.5544   1.0000
   0.500   0.4180   0.01232   0.00566  -0.0497   0.5506   1.0000
   0.750   0.4443   0.01251   0.00577  -0.0494   0.5459   1.0000
   1.000   0.4707   0.01266   0.00586  -0.0491   0.5408   1.0000
   1.250   0.4970   0.01280   0.00587  -0.0486   0.5366   1.0000
   1.500   0.5234   0.01299   0.00590  -0.0481   0.5331   1.0000
   1.750   0.5497   0.01318   0.00611  -0.0479   0.5277   1.0000
   2.000   0.5762   0.01334   0.00622  -0.0475   0.5229   1.0000
   2.250   0.6027   0.01348   0.00625  -0.0471   0.5189   1.0000
   2.500   0.6291   0.01370   0.00641  -0.0468   0.5147   1.0000
   2.750   0.6554   0.01390   0.00664  -0.0465   0.5093   1.0000
   3.000   0.6820   0.01404   0.00673  -0.0462   0.5048   1.0000
   3.250   0.7088   0.01421   0.00678  -0.0458   0.5011   1.0000
   3.500   0.7349   0.01446   0.00709  -0.0456   0.4957   1.0000
   3.750   0.7613   0.01463   0.00726  -0.0453   0.4905   1.0000
   4.000   0.7882   0.01476   0.00732  -0.0450   0.4865   1.0000
   4.250   0.8145   0.01501   0.00757  -0.0447   0.4819   1.0000
   4.500   0.8406   0.01521   0.00783  -0.0445   0.4761   1.0000
   4.750   0.8674   0.01534   0.00791  -0.0442   0.4716   1.0000
   5.000   0.8942   0.01554   0.00807  -0.0439   0.4675   1.0000
   5.250   0.9197   0.01578   0.00844  -0.0437   0.4611   1.0000
   5.500   0.9464   0.01590   0.00854  -0.0434   0.4562   1.0000
   5.750   0.9734   0.01607   0.00864  -0.0431   0.4521   1.0000
   6.000   0.9984   0.01633   0.00906  -0.0429   0.4453   1.0000
   6.250   1.0251   0.01643   0.00916  -0.0426   0.4402   1.0000
   6.500   1.0515   0.01662   0.00934  -0.0423   0.4352   1.0000
   6.750   1.0766   0.01684   0.00969  -0.0420   0.4284   1.0000
   7.000   1.1035   0.01690   0.00971  -0.0417   0.4232   1.0000
   7.250   1.1284   0.01715   0.01008  -0.0414   0.4164   1.0000
   7.500   1.1542   0.01723   0.01020  -0.0411   0.4098   1.0000
   7.750   1.1799   0.01740   0.01040  -0.0407   0.4035   1.0000
   8.000   1.2046   0.01755   0.01064  -0.0403   0.3957   1.0000
   8.250   1.2303   0.01769   0.01078  -0.0400   0.3891   1.0000
   8.500   1.2543   0.01788   0.01110  -0.0395   0.3806   1.0000
   8.750   1.2791   0.01806   0.01130  -0.0391   0.3732   1.0000
   9.000   1.3026   0.01825   0.01160  -0.0386   0.3643   1.0000
   9.250   1.3259   0.01851   0.01194  -0.0381   0.3554   1.0000
   9.500   1.3495   0.01870   0.01213  -0.0375   0.3464   1.0000
   9.750   1.3707   0.01903   0.01262  -0.0368   0.3357   1.0000
  10.000   1.3922   0.01936   0.01302  -0.0361   0.3254   1.0000
  10.250   1.4129   0.01972   0.01339  -0.0353   0.3147   1.0000
  10.500   1.4317   0.02016   0.01393  -0.0344   0.3025   1.0000
  10.750   1.4489   0.02069   0.01456  -0.0333   0.2895   1.0000
  11.000   1.4644   0.02131   0.01525  -0.0321   0.2762   1.0000
  11.250   1.4773   0.02204   0.01604  -0.0306   0.2623   1.0000
  11.500   1.4867   0.02292   0.01696  -0.0289   0.2482   1.0000
  11.750   1.4906   0.02396   0.01804  -0.0265   0.2347   1.0000
  12.000   1.4885   0.02530   0.01940  -0.0239   0.2224   1.0000
  12.250   1.4848   0.02710   0.02121  -0.0221   0.2103   1.0000
  12.500   1.4796   0.02934   0.02346  -0.0209   0.1982   1.0000
  12.750   1.4738   0.03192   0.02605  -0.0202   0.1859   1.0000
  13.000   1.4678   0.03475   0.02891  -0.0198   0.1739   1.0000
  13.250   1.4606   0.03782   0.03201  -0.0196   0.1625   1.0000
  13.500   1.4523   0.04112   0.03531  -0.0195   0.1522   1.0000
  13.750   1.4419   0.04468   0.03883  -0.0196   0.1431   1.0000
  14.000   1.4334   0.04821   0.04239  -0.0198   0.1336   1.0000
  14.250   1.4251   0.05177   0.04599  -0.0201   0.1250   1.0000
  14.500   1.4138   0.05568   0.04984  -0.0205   0.1177   1.0000
  14.750   1.4068   0.05944   0.05368  -0.0212   0.1095   1.0000
  15.000   1.3988   0.06337   0.05762  -0.0219   0.1025   1.0000
  15.250   1.3910   0.06743   0.06169  -0.0228   0.0960   1.0000
  15.500   1.3850   0.07134   0.06567  -0.0237   0.0895   1.0000
  15.750   1.3772   0.07555   0.06985  -0.0248   0.0839   1.0000
  16.000   1.3722   0.07955   0.07394  -0.0258   0.0782   1.0000
  16.250   1.3661   0.08371   0.07808  -0.0270   0.0733   1.0000
  16.500   1.3618   0.08774   0.08219  -0.0281   0.0686   1.0000
  16.750   1.3567   0.09194   0.08642  -0.0295   0.0644   1.0000
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