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EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 329 AIRFOIL (e329-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.92 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e329-il-1000000.txt
Download as CSV file: xf-e329-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 329 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3648   0.12209   0.12039  -0.0231   1.0000   0.0084
 -11.500  -0.3647   0.11777   0.11609  -0.0243   1.0000   0.0085
 -11.250  -0.3620   0.11446   0.11279  -0.0250   1.0000   0.0086
 -11.000  -0.3582   0.11141   0.10976  -0.0256   1.0000   0.0086
 -10.750  -0.3543   0.10843   0.10679  -0.0262   1.0000   0.0087
 -10.500  -0.3511   0.10534   0.10372  -0.0271   1.0000   0.0088
  -8.250  -0.3026   0.06133   0.05962  -0.0706   0.9249   0.0096
  -8.000  -0.2928   0.05653   0.05432  -0.0751   0.8316   0.0096
  -7.750  -0.2999   0.05375   0.05129  -0.0728   0.7902   0.0098
  -7.500  -0.3025   0.05079   0.04813  -0.0707   0.7623   0.0098
  -7.250  -0.3020   0.04774   0.04488  -0.0686   0.7401   0.0100
  -7.000  -0.2992   0.04399   0.04090  -0.0661   0.7217   0.0105
  -6.750  -0.2909   0.03928   0.03586  -0.0631   0.7062   0.0109
  -6.500  -0.2825   0.03599   0.03229  -0.0604   0.6905   0.0110
  -6.250  -0.2845   0.03109   0.02705  -0.0569   0.6780   0.0112
  -6.000  -0.2620   0.01550   0.01158  -0.0527   0.6441   0.0114
  -5.750  -0.2472   0.01393   0.00987  -0.0514   0.6325   0.0116
  -5.500  -0.2311   0.01243   0.00819  -0.0500   0.6211   0.0118
  -5.250  -0.2138   0.01096   0.00653  -0.0487   0.6098   0.0121
  -5.000  -0.1957   0.00937   0.00470  -0.0471   0.5995   0.0128
  -4.750  -0.1748   0.00831   0.00310  -0.0447   0.5894   0.0140
  -4.500  -0.1576   0.00621   0.00088  -0.0438   0.5808   0.0146
  -4.250  -0.1340   0.01456   0.00824  -0.0434   0.5838   0.0086
  -4.000  -0.1091   0.01337   0.00694  -0.0427   0.5735   0.0080
  -3.750  -0.0846   0.01233   0.00576  -0.0419   0.5636   0.0077
  -3.500  -0.0604   0.01170   0.00503  -0.0410   0.5538   0.0076
  -3.250  -0.0364   0.01120   0.00444  -0.0401   0.5438   0.0075
  -3.000  -0.0124   0.01075   0.00391  -0.0393   0.5350   0.0076
  -2.750   0.0118   0.01041   0.00348  -0.0384   0.5261   0.0078
  -2.500   0.0368   0.01011   0.00314  -0.0378   0.5178   0.0080
  -2.250   0.0619   0.00992   0.00287  -0.0372   0.5090   0.0083
  -2.000   0.0869   0.00962   0.00254  -0.0365   0.5011   0.0097
  -1.750   0.1122   0.00946   0.00233  -0.0360   0.4930   0.0122
  -1.500   0.1382   0.00927   0.00214  -0.0355   0.4861   0.0199
  -1.250   0.1631   0.00907   0.00203  -0.0350   0.4786   0.0502
  -1.000   0.1886   0.00886   0.00195  -0.0345   0.4720   0.0950
  -0.750   0.1998   0.00740   0.00172  -0.0321   0.4659   0.4875
  -0.500   0.2100   0.00647   0.00180  -0.0286   0.4601   0.8012
  -0.250   0.2362   0.00662   0.00193  -0.0279   0.4541   0.8271
   0.000   0.2621   0.00680   0.00209  -0.0272   0.4479   0.8422
   0.250   0.2883   0.00695   0.00223  -0.0265   0.4421   0.8524
   0.500   0.3154   0.00709   0.00232  -0.0262   0.4363   0.8592
   0.750   0.3413   0.00721   0.00241  -0.0256   0.4304   0.8655
   1.000   0.3677   0.00737   0.00256  -0.0250   0.4257   0.8730
   1.250   0.3955   0.00745   0.00258  -0.0250   0.4202   0.8753
   1.500   0.4231   0.00753   0.00259  -0.0251   0.4147   0.8762
   1.750   0.4511   0.00752   0.00256  -0.0252   0.4106   0.8774
   2.000   0.4790   0.00755   0.00256  -0.0253   0.4057   0.8784
   2.250   0.5064   0.00762   0.00258  -0.0252   0.4009   0.8795
   2.500   0.5339   0.00768   0.00262  -0.0252   0.3966   0.8806
   2.750   0.5619   0.00772   0.00265  -0.0253   0.3926   0.8817
   3.000   0.5894   0.00779   0.00268  -0.0254   0.3878   0.8827
   3.250   0.6164   0.00790   0.00274  -0.0253   0.3831   0.8838
   3.500   0.6444   0.00794   0.00279  -0.0255   0.3797   0.8849
   3.750   0.6721   0.00800   0.00284  -0.0256   0.3755   0.8860
   4.000   0.6993   0.00809   0.00290  -0.0256   0.3712   0.8873
   4.250   0.7261   0.00821   0.00299  -0.0255   0.3667   0.8887
   4.500   0.7540   0.00825   0.00306  -0.0257   0.3632   0.8899
   4.750   0.7815   0.00833   0.00313  -0.0258   0.3592   0.8909
   5.000   0.8083   0.00845   0.00321  -0.0257   0.3545   0.8919
   5.250   0.8350   0.00853   0.00330  -0.0257   0.3504   0.8932
   5.500   0.8623   0.00858   0.00338  -0.0257   0.3467   0.8945
   5.750   0.8889   0.00867   0.00347  -0.0257   0.3423   0.8958
   6.000   0.9145   0.00882   0.00360  -0.0254   0.3372   0.8972
   6.250   0.9416   0.00889   0.00370  -0.0255   0.3336   0.8986
   6.500   0.9682   0.00898   0.00381  -0.0254   0.3290   0.9001
   6.750   0.9937   0.00913   0.00395  -0.0252   0.3237   0.9019
   7.000   1.0201   0.00924   0.00408  -0.0251   0.3191   0.9036
   7.250   1.0464   0.00934   0.00421  -0.0251   0.3135   0.9052
   7.500   1.0715   0.00952   0.00437  -0.0248   0.3078   0.9068
   7.750   1.0976   0.00962   0.00450  -0.0247   0.3026   0.9084
   8.000   1.1225   0.00975   0.00465  -0.0244   0.2964   0.9104
   8.250   1.1469   0.00991   0.00483  -0.0240   0.2907   0.9124
   8.500   1.1717   0.01006   0.00500  -0.0237   0.2835   0.9144
   8.750   1.1952   0.01026   0.00521  -0.0232   0.2766   0.9168
   9.000   1.2195   0.01043   0.00540  -0.0229   0.2691   0.9192
   9.250   1.2425   0.01067   0.00563  -0.0223   0.2608   0.9216
   9.500   1.2646   0.01091   0.00587  -0.0216   0.2512   0.9245
   9.750   1.2860   0.01115   0.00612  -0.0207   0.2411   0.9278
  10.000   1.3063   0.01144   0.00642  -0.0197   0.2312   0.9316
  10.250   1.3252   0.01180   0.00675  -0.0184   0.2189   0.9357
  10.500   1.3425   0.01218   0.00710  -0.0169   0.2061   0.9403
  10.750   1.3579   0.01258   0.00749  -0.0150   0.1936   0.9465
  11.000   1.3712   0.01296   0.00786  -0.0128   0.1817   0.9543
  11.250   1.3854   0.01340   0.00830  -0.0108   0.1694   0.9661
  11.500   1.4099   0.01409   0.00895  -0.0115   0.1541   0.9788
  11.750   1.4303   0.01480   0.00963  -0.0113   0.1398   1.0000
  12.000   1.4405   0.01551   0.01029  -0.0091   0.1278   1.0000
  12.250   1.4495   0.01627   0.01101  -0.0069   0.1167   1.0000
  12.500   1.4581   0.01705   0.01178  -0.0047   0.1072   1.0000
  12.750   1.4652   0.01794   0.01266  -0.0024   0.0988   1.0000
  13.000   1.4692   0.01904   0.01374  -0.0001   0.0901   1.0000
  13.250   1.4728   0.02026   0.01496   0.0020   0.0826   1.0000
  13.500   1.4771   0.02157   0.01629   0.0037   0.0762   1.0000
  13.750   1.4770   0.02331   0.01802   0.0053   0.0690   1.0000
  14.000   1.4804   0.02498   0.01973   0.0064   0.0643   1.0000
  14.250   1.4799   0.02711   0.02188   0.0073   0.0591   1.0000
  14.500   1.4799   0.02937   0.02418   0.0078   0.0544   1.0000
  14.750   1.4763   0.03209   0.02692   0.0082   0.0490   1.0000
  15.000   1.4741   0.03481   0.02969   0.0083   0.0457   1.0000
  15.250   1.4690   0.03790   0.03283   0.0083   0.0426   1.0000
  15.500   1.4661   0.04083   0.03583   0.0081   0.0398   1.0000
  15.750   1.4563   0.04456   0.03960   0.0078   0.0366   1.0000
  16.250   1.4437   0.05152   0.04671   0.0069   0.0327   1.0000
  16.500   1.4326   0.05565   0.05089   0.0061   0.0304   1.0000
  16.750   1.4247   0.05953   0.05485   0.0054   0.0287   1.0000
  17.000   1.4180   0.06335   0.05874   0.0045   0.0273   1.0000
  17.250   1.4068   0.06778   0.06322   0.0034   0.0255   1.0000
  17.500   1.3973   0.07208   0.06760   0.0023   0.0244   1.0000
  17.750   1.3905   0.07612   0.07172   0.0012   0.0235   1.0000
  18.000   1.3837   0.08019   0.07586   0.0000   0.0222   1.0000
  18.250   1.3733   0.08482   0.08054  -0.0015   0.0208   1.0000
  18.500   1.3643   0.08936   0.08516  -0.0030   0.0201   1.0000
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