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EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 330 AIRFOIL (e330-il)
Reynolds number: 1,000,000
Max Cl/Cd: 84.76 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e330-il-1000000-n5.txt
Download as CSV file: xf-e330-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 330 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5342   0.08691   0.08486   0.0006   0.7850   0.0051
  -9.000  -0.5457   0.08121   0.07907  -0.0041   0.7559   0.0051
  -8.750  -0.5591   0.07642   0.07418  -0.0066   0.7333   0.0051
  -6.250  -0.5991   0.03267   0.02849   0.0165   0.6009   0.0029
  -6.000  -0.5976   0.02540   0.02062   0.0220   0.5942   0.0028
  -5.750  -0.5867   0.02006   0.01460   0.0260   0.5844   0.0026
  -5.500  -0.5661   0.01736   0.01142   0.0279   0.5734   0.0026
  -5.250  -0.5421   0.01591   0.00970   0.0289   0.5617   0.0026
  -5.000  -0.5175   0.01468   0.00823   0.0297   0.5505   0.0026
  -4.750  -0.4926   0.01382   0.00721   0.0305   0.5391   0.0026
  -4.500  -0.4678   0.01312   0.00636   0.0312   0.5279   0.0026
  -4.250  -0.4433   0.01247   0.00557   0.0321   0.5176   0.0027
  -4.000  -0.4184   0.01201   0.00501   0.0328   0.5075   0.0027
  -3.750  -0.3936   0.01158   0.00449   0.0335   0.4977   0.0028
  -3.500  -0.3687   0.01121   0.00403   0.0342   0.4876   0.0029
  -3.250  -0.3434   0.01090   0.00365   0.0348   0.4783   0.0030
  -3.000  -0.3178   0.01066   0.00336   0.0354   0.4693   0.0031
  -2.750  -0.2931   0.01031   0.00293   0.0361   0.4607   0.0037
  -2.500  -0.2672   0.01013   0.00271   0.0366   0.4522   0.0041
  -2.250  -0.2412   0.00998   0.00251   0.0371   0.4441   0.0047
  -2.000  -0.2150   0.00983   0.00231   0.0375   0.4357   0.0050
  -1.750  -0.1889   0.00969   0.00214   0.0379   0.4279   0.0063
  -1.500  -0.1626   0.00956   0.00199   0.0383   0.4204   0.0089
  -1.250  -0.1370   0.00937   0.00185   0.0388   0.4139   0.0247
  -1.000  -0.1117   0.00917   0.00174   0.0393   0.4060   0.0553
  -0.750  -0.0879   0.00885   0.00165   0.0401   0.3997   0.1302
  -0.500  -0.0622   0.00869   0.00157   0.0405   0.3935   0.1692
  -0.250  -0.0407   0.00823   0.00145   0.0417   0.3873   0.2860
   0.000  -0.0600   0.00587   0.00115   0.0513   0.3846   0.8314
   0.250  -0.0350   0.00595   0.00133   0.0523   0.3782   0.8897
   0.500  -0.0088   0.00605   0.00138   0.0529   0.3723   0.9026
   0.750   0.0190   0.00614   0.00145   0.0531   0.3671   0.9097
   1.000   0.0454   0.00625   0.00150   0.0535   0.3606   0.9172
   1.250   0.0740   0.00635   0.00156   0.0535   0.3553   0.9205
   1.500   0.1020   0.00643   0.00160   0.0535   0.3500   0.9235
   2.000   0.1560   0.00655   0.00163   0.0539   0.3392   0.9281
   2.250   0.1829   0.00661   0.00165   0.0541   0.3340   0.9297
   2.500   0.2116   0.00668   0.00168   0.0539   0.3290   0.9308
   2.750   0.2401   0.00674   0.00173   0.0538   0.3236   0.9320
   3.000   0.2682   0.00683   0.00178   0.0537   0.3183   0.9332
   3.250   0.2963   0.00690   0.00183   0.0536   0.3133   0.9343
   3.500   0.3243   0.00697   0.00189   0.0535   0.3081   0.9354
   3.750   0.3519   0.00708   0.00196   0.0535   0.3024   0.9372
   4.000   0.3795   0.00715   0.00203   0.0535   0.2975   0.9386
   4.250   0.4065   0.00724   0.00209   0.0536   0.2918   0.9402
   4.500   0.4332   0.00733   0.00216   0.0537   0.2861   0.9417
   4.750   0.4595   0.00741   0.00225   0.0540   0.2806   0.9434
   5.000   0.4871   0.00753   0.00234   0.0539   0.2741   0.9448
   5.250   0.5155   0.00764   0.00247   0.0537   0.2684   0.9467
   5.500   0.5430   0.00776   0.00257   0.0536   0.2616   0.9475
   5.750   0.5705   0.00787   0.00269   0.0535   0.2549   0.9483
   6.000   0.5977   0.00801   0.00280   0.0535   0.2474   0.9491
   6.250   0.6248   0.00814   0.00293   0.0534   0.2394   0.9500
   6.500   0.6514   0.00830   0.00308   0.0535   0.2312   0.9510
   6.750   0.6782   0.00844   0.00322   0.0535   0.2235   0.9520
   7.000   0.7043   0.00861   0.00338   0.0536   0.2143   0.9531
   7.250   0.7299   0.00882   0.00355   0.0538   0.2040   0.9543
   7.500   0.7553   0.00901   0.00374   0.0540   0.1934   0.9555
   7.750   0.7797   0.00925   0.00395   0.0543   0.1808   0.9570
   8.000   0.8044   0.00949   0.00417   0.0546   0.1699   0.9583
   8.250   0.8300   0.00982   0.00445   0.0547   0.1546   0.9593
   8.500   0.8551   0.01017   0.00477   0.0547   0.1397   0.9603
   8.750   0.8796   0.01056   0.00511   0.0549   0.1252   0.9615
   9.000   0.9041   0.01093   0.00545   0.0550   0.1131   0.9627
   9.250   0.9274   0.01138   0.00585   0.0553   0.0983   0.9642
   9.500   0.9499   0.01187   0.00629   0.0557   0.0831   0.9659
   9.750   0.9717   0.01236   0.00675   0.0563   0.0707   0.9679
  10.000   0.9927   0.01281   0.00718   0.0570   0.0619   0.9701
  10.250   1.0128   0.01328   0.00764   0.0578   0.0537   0.9723
  10.500   1.0374   0.01380   0.00816   0.0576   0.0455   0.9735
  10.750   1.0618   0.01435   0.00871   0.0574   0.0390   0.9748
  11.000   1.0837   0.01508   0.00940   0.0573   0.0296   0.9766
  11.250   1.1050   0.01582   0.01013   0.0574   0.0225   0.9787
  11.500   1.1240   0.01665   0.01094   0.0577   0.0157   0.9812
  11.750   1.1425   0.01724   0.01158   0.0584   0.0141   0.9842
  12.000   1.1638   0.01817   0.01251   0.0578   0.0099   0.9855
  12.250   1.1877   0.01893   0.01334   0.0570   0.0092   0.9866
  12.500   1.2062   0.01997   0.01441   0.0566   0.0069   0.9885
  12.750   1.2232   0.02102   0.01553   0.0562   0.0059   0.9910
  13.000   1.2375   0.02229   0.01687   0.0556   0.0052   0.9941
  13.250   1.2518   0.02395   0.01862   0.0540   0.0042   0.9969
  13.500   1.2654   0.02605   0.02081   0.0517   0.0035   0.9992
  13.750   1.2687   0.02830   0.02314   0.0510   0.0030   1.0000
  14.000   1.2627   0.03062   0.02555   0.0520   0.0028   1.0000
  14.250   1.2571   0.03333   0.02833   0.0523   0.0025   1.0000
  14.500   1.2506   0.03641   0.03150   0.0520   0.0021   1.0000
  14.750   1.2429   0.03980   0.03497   0.0515   0.0017   1.0000
  15.250   1.2282   0.04681   0.04216   0.0500   0.0016   1.0000
  15.500   1.2213   0.05034   0.04577   0.0491   0.0016   1.0000
  15.750   1.2127   0.05416   0.04968   0.0480   0.0015   1.0000
  16.000   1.2021   0.05829   0.05390   0.0468   0.0015   1.0000
  16.250   1.1926   0.06245   0.05816   0.0454   0.0014   1.0000
  16.500   1.1775   0.06752   0.06331   0.0435   0.0011   1.0000
  16.750   1.1717   0.07143   0.06731   0.0421   0.0013   1.0000
  17.000   1.1577   0.07660   0.07256   0.0401   0.0010   1.0000
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