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EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 325 AIRFOIL (e325-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.15 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e325-il-1000000.txt
Download as CSV file: xf-e325-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 325 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5004   0.08119   0.07977  -0.0083   1.0000   0.0080
 -10.250  -0.5227   0.06988   0.06842  -0.0162   1.0000   0.0080
 -10.000  -0.5440   0.06311   0.06157  -0.0194   1.0000   0.0080
  -9.750  -0.5692   0.05711   0.05547  -0.0204   1.0000   0.0080
  -9.500  -0.5936   0.05184   0.05009  -0.0195   1.0000   0.0080
  -9.250  -0.6138   0.04795   0.04610  -0.0173   1.0000   0.0080
  -9.000  -0.6343   0.04404   0.04205  -0.0139   1.0000   0.0080
  -8.750  -0.6575   0.03992   0.03776  -0.0088   1.0000   0.0080
  -8.500  -0.6739   0.03673   0.03440  -0.0037   1.0000   0.0080
  -8.250  -0.7056   0.03021   0.02759   0.0029   1.0000   0.0082
  -7.500  -0.7647   0.02522   0.02108   0.0235   1.0000   0.0061
  -7.000  -0.6645   0.01870   0.01493   0.0143   0.8068   0.0089
  -6.750  -0.6539   0.01635   0.01224   0.0172   0.7784   0.0094
  -6.000  -0.6023   0.01575   0.00973   0.0237   0.7409   0.0070
  -5.750  -0.5773   0.01476   0.00855   0.0244   0.7186   0.0069
  -5.500  -0.5532   0.01405   0.00770   0.0252   0.6980   0.0069
  -5.250  -0.5297   0.01355   0.00709   0.0261   0.6782   0.0071
  -5.000  -0.5069   0.01300   0.00644   0.0271   0.6603   0.0072
  -4.750  -0.4842   0.01254   0.00588   0.0282   0.6436   0.0074
  -4.500  -0.4609   0.01221   0.00547   0.0291   0.6283   0.0076
  -4.250  -0.4379   0.01186   0.00503   0.0301   0.6136   0.0079
  -4.000  -0.4162   0.01140   0.00448   0.0314   0.5990   0.0082
  -3.750  -0.3933   0.01107   0.00409   0.0324   0.5857   0.0083
  -3.500  -0.3709   0.01070   0.00365   0.0336   0.5734   0.0087
  -3.250  -0.3472   0.01046   0.00335   0.0345   0.5605   0.0096
  -3.000  -0.3236   0.01020   0.00303   0.0354   0.5484   0.0115
  -2.750  -0.3015   0.00984   0.00272   0.0367   0.5373   0.0276
  -2.500  -0.2803   0.00947   0.00251   0.0379   0.5268   0.0725
  -2.250  -0.2589   0.00911   0.00234   0.0391   0.5159   0.1288
  -2.000  -0.2437   0.00842   0.00210   0.0414   0.5065   0.2598
  -1.750  -0.2434   0.00706   0.00170   0.0465   0.4986   0.5179
  -1.500  -0.2493   0.00580   0.00149   0.0535   0.4920   0.7811
  -1.250  -0.2259   0.00595   0.00169   0.0549   0.4824   0.8266
  -1.000  -0.1995   0.00613   0.00184   0.0555   0.4731   0.8419
  -0.750  -0.1730   0.00632   0.00197   0.0561   0.4637   0.8527
  -0.500  -0.1453   0.00654   0.00217   0.0565   0.4551   0.8618
  -0.250  -0.1181   0.00665   0.00222   0.0568   0.4466   0.8669
   0.000  -0.0892   0.00686   0.00241   0.0569   0.4377   0.8726
   0.250  -0.0623   0.00707   0.00257   0.0573   0.4300   0.8786
   0.500  -0.0348   0.00711   0.00255   0.0574   0.4223   0.8812
   0.750  -0.0068   0.00711   0.00249   0.0573   0.4147   0.8823
   1.000   0.0216   0.00712   0.00246   0.0572   0.4072   0.8833
   1.250   0.0497   0.00717   0.00245   0.0570   0.4002   0.8843
   1.500   0.0780   0.00718   0.00244   0.0569   0.3937   0.8851
   1.750   0.1058   0.00724   0.00243   0.0568   0.3865   0.8861
   2.000   0.1341   0.00726   0.00244   0.0567   0.3805   0.8871
   2.250   0.1620   0.00730   0.00244   0.0565   0.3743   0.8881
   2.500   0.1899   0.00735   0.00245   0.0564   0.3684   0.8891
   2.750   0.2180   0.00737   0.00245   0.0563   0.3625   0.8900
   3.000   0.2456   0.00744   0.00248   0.0562   0.3564   0.8910
   3.250   0.2735   0.00748   0.00251   0.0561   0.3515   0.8922
   3.500   0.3014   0.00752   0.00253   0.0559   0.3456   0.8932
   3.750   0.3288   0.00761   0.00257   0.0558   0.3395   0.8941
   4.000   0.3570   0.00764   0.00261   0.0556   0.3347   0.8948
   4.250   0.3847   0.00771   0.00265   0.0555   0.3287   0.8956
   4.500   0.4122   0.00777   0.00269   0.0554   0.3229   0.8964
   4.750   0.4401   0.00778   0.00272   0.0552   0.3176   0.8975
   5.000   0.4675   0.00786   0.00279   0.0551   0.3115   0.8985
   5.250   0.4951   0.00793   0.00287   0.0550   0.3064   0.8996
   5.500   0.5227   0.00800   0.00295   0.0549   0.3005   0.9006
   5.750   0.5497   0.00813   0.00306   0.0549   0.2939   0.9017
   6.000   0.5775   0.00818   0.00314   0.0547   0.2887   0.9027
   6.250   0.6046   0.00830   0.00325   0.0546   0.2819   0.9038
   6.500   0.6318   0.00839   0.00336   0.0546   0.2757   0.9050
   6.750   0.6588   0.00851   0.00347   0.0545   0.2682   0.9061
   7.000   0.6857   0.00863   0.00360   0.0544   0.2608   0.9073
   7.250   0.7123   0.00877   0.00373   0.0544   0.2530   0.9085
   7.500   0.7389   0.00891   0.00388   0.0544   0.2456   0.9097
   7.750   0.7651   0.00908   0.00405   0.0544   0.2369   0.9108
   8.000   0.7914   0.00923   0.00421   0.0544   0.2287   0.9119
   8.250   0.8169   0.00941   0.00438   0.0545   0.2190   0.9136
   8.500   0.8421   0.00961   0.00458   0.0547   0.2086   0.9153
   8.750   0.8669   0.00984   0.00481   0.0549   0.1963   0.9169
   9.000   0.8912   0.01011   0.00506   0.0552   0.1834   0.9186
   9.250   0.9144   0.01045   0.00536   0.0557   0.1681   0.9204
   9.500   0.9362   0.01088   0.00572   0.0563   0.1501   0.9224
   9.750   0.9575   0.01132   0.00610   0.0569   0.1318   0.9245
  10.000   0.9789   0.01174   0.00649   0.0576   0.1186   0.9265
  10.250   0.9982   0.01226   0.00694   0.0585   0.1023   0.9290
  10.500   1.0158   0.01284   0.00746   0.0597   0.0863   0.9319
  10.750   1.0320   0.01345   0.00801   0.0611   0.0704   0.9352
  11.000   1.0493   0.01396   0.00851   0.0624   0.0618   0.9387
  11.250   1.0645   0.01454   0.00907   0.0639   0.0527   0.9427
  11.500   1.0786   0.01511   0.00965   0.0656   0.0457   0.9478
  11.750   1.0914   0.01567   0.01023   0.0675   0.0394   0.9537
  12.000   1.1027   0.01622   0.01082   0.0696   0.0347   0.9607
  12.250   1.1127   0.01693   0.01155   0.0717   0.0299   0.9706
  12.500   1.1333   0.01789   0.01254   0.0710   0.0251   0.9770
  12.750   1.1540   0.01901   0.01368   0.0698   0.0208   0.9837
  13.000   1.1779   0.02030   0.01502   0.0675   0.0175   0.9869
  13.250   1.1992   0.02174   0.01653   0.0652   0.0153   0.9914
  13.500   1.2172   0.02361   0.01845   0.0625   0.0132   0.9993
  13.750   1.2163   0.02530   0.02021   0.0636   0.0126   1.0000
  14.000   1.2150   0.02730   0.02227   0.0642   0.0118   1.0000
  14.250   1.2127   0.02973   0.02476   0.0643   0.0110   1.0000
  14.500   1.2092   0.03248   0.02760   0.0641   0.0104   1.0000
  14.750   1.2090   0.03502   0.03021   0.0637   0.0098   1.0000
  15.000   1.2052   0.03801   0.03330   0.0631   0.0097   1.0000
  15.250   1.2009   0.04111   0.03645   0.0623   0.0089   1.0000
  15.500   1.1916   0.04484   0.04025   0.0613   0.0082   1.0000
  15.750   1.1851   0.04831   0.04381   0.0604   0.0081   1.0000
  16.000   1.1738   0.05238   0.04798   0.0592   0.0081   1.0000
  16.250   1.1656   0.05619   0.05188   0.0580   0.0079   1.0000
  16.500   1.1552   0.06042   0.05621   0.0566   0.0079   1.0000
  16.750   1.1493   0.06416   0.06003   0.0552   0.0076   1.0000
  17.000   1.1403   0.06840   0.06435   0.0537   0.0073   1.0000
  17.250   1.1305   0.07281   0.06883   0.0520   0.0071   1.0000
  17.500   1.1220   0.07712   0.07321   0.0504   0.0068   1.0000
  17.750   1.1103   0.08196   0.07814   0.0485   0.0067   1.0000
  18.000   1.0995   0.08674   0.08300   0.0465   0.0064   1.0000
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