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EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 330 AIRFOIL (e330-il)
Reynolds number: 50,000
Max Cl/Cd: 17.19 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e330-il-50000.txt
Download as CSV file: xf-e330-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5206   0.11211   0.10599   0.0195   1.0000   0.2250
  -9.000  -0.5241   0.10877   0.10274   0.0186   1.0000   0.2366
  -8.750  -0.5446   0.10667   0.10077   0.0161   1.0000   0.2480
  -8.500  -0.5144   0.10158   0.09568   0.0191   1.0000   0.2676
  -8.250  -0.5088   0.09821   0.09237   0.0198   1.0000   0.2865
  -8.000  -0.5235   0.09567   0.08995   0.0194   1.0000   0.3059
  -7.750  -0.5088   0.09207   0.08639   0.0218   1.0000   0.3342
  -7.500  -0.5064   0.08924   0.08364   0.0239   1.0000   0.3645
  -7.250  -0.4886   0.08627   0.08072   0.0277   1.0000   0.4084
  -7.000  -0.4510   0.08324   0.07769   0.0337   1.0000   0.4808
  -5.750  -0.4174   0.06594   0.06082   0.0370   1.0000   0.5594
  -5.500  -0.4772   0.06120   0.05636   0.0335   1.0000   0.5020
  -5.250  -0.5303   0.05559   0.05077   0.0263   1.0000   0.4292
  -5.000  -0.5166   0.04718   0.04005   0.0111   1.0000   0.1575
  -4.750  -0.4996   0.04441   0.03642   0.0141   1.0000   0.1249
  -4.500  -0.4867   0.04143   0.03343   0.0161   1.0000   0.1199
  -4.250  -0.4838   0.04020   0.03161   0.0207   1.0000   0.1116
  -4.000  -0.4837   0.03863   0.03001   0.0240   1.0000   0.1102
  -3.750  -0.4818   0.03724   0.02849   0.0270   1.0000   0.1083
  -3.500  -0.4758   0.03584   0.02686   0.0297   1.0000   0.1061
  -3.250  -0.0381   0.02111   0.01372  -0.0218   1.0000   1.0000
  -3.000  -0.0141   0.02098   0.01333  -0.0230   1.0000   1.0000
  -2.750  -0.0003   0.02134   0.01358  -0.0236   1.0000   1.0000
  -2.500   0.0299   0.02189   0.01387  -0.0278   0.9737   1.0000
  -2.250   0.1088   0.02147   0.01290  -0.0386   0.9303   1.0000
  -2.000   0.1547   0.02144   0.01246  -0.0424   0.8915   1.0000
  -1.750   0.1794   0.02171   0.01244  -0.0419   0.8596   1.0000
  -1.500   0.1990   0.02207   0.01256  -0.0404   0.8329   1.0000
  -1.250   0.2179   0.02244   0.01269  -0.0386   0.8113   1.0000
  -1.000   0.2379   0.02284   0.01293  -0.0375   0.7897   1.0000
  -0.750   0.2579   0.02323   0.01316  -0.0362   0.7715   1.0000
  -0.500   0.2780   0.02363   0.01342  -0.0349   0.7549   1.0000
  -0.250   0.2982   0.02406   0.01370  -0.0336   0.7392   1.0000
   0.000   0.3192   0.02453   0.01406  -0.0326   0.7244   1.0000
   0.250   0.3408   0.02502   0.01445  -0.0318   0.7101   1.0000
   0.500   0.3623   0.02556   0.01491  -0.0311   0.6964   1.0000
   0.750   0.3840   0.02615   0.01546  -0.0305   0.6833   1.0000
   1.000   0.4056   0.02678   0.01605  -0.0299   0.6707   1.0000
   1.250   0.4272   0.02745   0.01669  -0.0293   0.6591   1.0000
   1.500   0.4480   0.02806   0.01725  -0.0283   0.6485   1.0000
   1.750   0.4691   0.02875   0.01792  -0.0275   0.6374   1.0000
   2.000   0.4905   0.02969   0.01890  -0.0274   0.6260   1.0000
   2.250   0.5111   0.03058   0.01981  -0.0269   0.6156   1.0000
   2.500   0.5311   0.03120   0.02041  -0.0254   0.6068   1.0000
   2.750   0.5511   0.03247   0.02178  -0.0256   0.5957   1.0000
   3.000   0.5700   0.03366   0.02303  -0.0252   0.5856   1.0000
   3.250   0.5898   0.03432   0.02367  -0.0236   0.5775   1.0000
   3.500   0.6064   0.03605   0.02554  -0.0239   0.5668   1.0000
   3.750   0.6231   0.03745   0.02704  -0.0232   0.5576   1.0000
   4.000   0.6413   0.03845   0.02809  -0.0219   0.5491   1.0000
   4.250   0.6525   0.04069   0.03047  -0.0220   0.5391   1.0000
   4.500   0.6693   0.04182   0.03165  -0.0205   0.5309   1.0000
   4.750   0.6793   0.04395   0.03389  -0.0200   0.5214   1.0000
   5.000   0.6843   0.04655   0.03660  -0.0194   0.5124   1.0000
   5.250   0.7045   0.04722   0.03735  -0.0173   0.5045   1.0000
   5.500   0.6915   0.05159   0.04184  -0.0173   0.4957   1.0000
   5.750   0.7085   0.05265   0.04295  -0.0153   0.4874   1.0000
   6.000   0.6834   0.05756   0.04791  -0.0147   0.4807   1.0000
   6.250   0.6965   0.05907   0.04949  -0.0128   0.4724   1.0000
   6.500   0.6594   0.06421   0.05456  -0.0112   0.4687   1.0000
   6.750   0.6321   0.06778   0.05807  -0.0083   0.4664   1.0000
   7.000   0.6449   0.06957   0.05993  -0.0067   0.4579   1.0000
   7.250   0.6190   0.07325   0.06354  -0.0044   0.4573   1.0000
   7.500   0.6035   0.07680   0.06706  -0.0031   0.4575   1.0000
   7.750   0.5974   0.08044   0.07074  -0.0027   0.4608   1.0000
   8.000   0.4883   0.08941   0.07943  -0.0064   0.5685   1.0000
   8.250   0.4957   0.09176   0.08182  -0.0054   0.5547   1.0000
   8.500   0.5035   0.09431   0.08445  -0.0047   0.5427   1.0000
   8.750   0.5133   0.09697   0.08717  -0.0041   0.5296   1.0000
   9.000   0.5233   0.09963   0.08989  -0.0034   0.5159   1.0000
   9.250   0.5422   0.10309   0.09345  -0.0033   0.5032   1.0000
   9.500   0.5516   0.10577   0.09620  -0.0026   0.4893   1.0000
   9.750   0.5503   0.10771   0.09820  -0.0014   0.4757   1.0000
  10.000   0.5439   0.10966   0.10016  -0.0003   0.4643   1.0000
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