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EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 327 AIRFOIL (e327-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.3 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e327-il-1000000-n5.txt
Download as CSV file: xf-e327-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 327 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4904   0.08003   0.07846  -0.0277   1.0000   0.0038
  -9.750  -0.5091   0.07156   0.06995  -0.0359   0.9693   0.0038
  -9.500  -0.5212   0.05843   0.05627  -0.0497   0.8569   0.0041
  -9.250  -0.5501   0.05439   0.05190  -0.0445   0.7972   0.0043
  -9.000  -0.5647   0.05177   0.04906  -0.0405   0.7640   0.0042
  -8.750  -0.5818   0.04666   0.04368  -0.0363   0.7412   0.0042
  -8.500  -0.5919   0.04188   0.03862  -0.0323   0.7240   0.0042
  -8.250  -0.6351   0.02828   0.02416  -0.0228   0.7173   0.0041
  -8.000  -0.6305   0.02461   0.02000  -0.0193   0.7008   0.0041
  -7.750  -0.6164   0.02262   0.01766  -0.0171   0.6830   0.0042
  -7.500  -0.5989   0.02105   0.01579  -0.0154   0.6665   0.0042
  -7.250  -0.5779   0.02021   0.01475  -0.0143   0.6512   0.0043
  -7.000  -0.5574   0.01899   0.01328  -0.0130   0.6371   0.0043
  -6.750  -0.5353   0.01806   0.01213  -0.0120   0.6227   0.0043
  -6.500  -0.5130   0.01694   0.01081  -0.0110   0.6099   0.0043
  -6.250  -0.4895   0.01609   0.00979  -0.0102   0.5982   0.0043
  -6.000  -0.4657   0.01533   0.00888  -0.0095   0.5865   0.0043
  -5.750  -0.4422   0.01446   0.00785  -0.0086   0.5749   0.0043
  -5.500  -0.4185   0.01380   0.00708  -0.0078   0.5626   0.0043
  -5.250  -0.3943   0.01333   0.00652  -0.0071   0.5527   0.0043
  -5.000  -0.3709   0.01280   0.00589  -0.0062   0.5427   0.0044
  -4.750  -0.3478   0.01228   0.00528  -0.0053   0.5319   0.0044
  -4.500  -0.3245   0.01183   0.00476  -0.0044   0.5227   0.0045
  -4.250  -0.3006   0.01152   0.00437  -0.0036   0.5127   0.0045
  -4.000  -0.2765   0.01119   0.00399  -0.0028   0.5045   0.0046
  -3.750  -0.2524   0.01091   0.00364  -0.0021   0.4956   0.0048
  -3.500  -0.2274   0.01070   0.00339  -0.0015   0.4867   0.0049
  -3.250  -0.2024   0.01051   0.00315  -0.0009   0.4783   0.0050
  -3.000  -0.1771   0.01034   0.00294  -0.0003   0.4706   0.0052
  -2.750  -0.1518   0.01018   0.00272   0.0002   0.4634   0.0058
  -2.500  -0.1261   0.01004   0.00255   0.0007   0.4555   0.0062
  -2.250  -0.1008   0.00990   0.00237   0.0012   0.4480   0.0080
  -2.000  -0.0749   0.00977   0.00223   0.0016   0.4411   0.0106
  -1.500  -0.0239   0.00949   0.00201   0.0026   0.4284   0.0364
  -1.250   0.0014   0.00935   0.00192   0.0030   0.4213   0.0587
  -1.000   0.0229   0.00891   0.00181   0.0041   0.4158   0.1607
  -0.750   0.0103   0.00635   0.00136   0.0113   0.4124   0.7434
  -0.500   0.0351   0.00636   0.00147   0.0122   0.4066   0.8010
  -0.250   0.0625   0.00643   0.00151   0.0124   0.4011   0.8136
   0.000   0.0899   0.00652   0.00157   0.0126   0.3952   0.8261
   0.250   0.1172   0.00663   0.00162   0.0128   0.3894   0.8355
   0.500   0.1449   0.00670   0.00168   0.0130   0.3849   0.8415
   0.750   0.1727   0.00679   0.00173   0.0131   0.3798   0.8466
   1.000   0.2009   0.00685   0.00173   0.0130   0.3742   0.8481
   1.250   0.2292   0.00690   0.00174   0.0128   0.3697   0.8490
   1.500   0.2576   0.00695   0.00174   0.0127   0.3651   0.8501
   1.750   0.2858   0.00701   0.00176   0.0125   0.3597   0.8511
   2.000   0.3140   0.00708   0.00178   0.0124   0.3552   0.8519
   2.250   0.3424   0.00713   0.00180   0.0122   0.3511   0.8527
   2.500   0.3705   0.00718   0.00183   0.0121   0.3462   0.8536
   2.750   0.3984   0.00726   0.00187   0.0120   0.3413   0.8545
   3.000   0.4266   0.00731   0.00192   0.0119   0.3376   0.8554
   3.250   0.4546   0.00737   0.00197   0.0117   0.3330   0.8564
   3.500   0.4824   0.00746   0.00203   0.0117   0.3280   0.8575
   3.750   0.5103   0.00754   0.00210   0.0115   0.3241   0.8585
   4.000   0.5382   0.00761   0.00216   0.0114   0.3195   0.8594
   4.250   0.5659   0.00771   0.00224   0.0113   0.3146   0.8604
   4.500   0.5935   0.00780   0.00233   0.0112   0.3101   0.8614
   4.750   0.6213   0.00788   0.00241   0.0111   0.3054   0.8625
   5.000   0.6488   0.00799   0.00250   0.0110   0.3000   0.8635
   5.250   0.6761   0.00810   0.00261   0.0109   0.2950   0.8645
   5.500   0.7037   0.00820   0.00270   0.0108   0.2896   0.8656
   5.750   0.7307   0.00834   0.00282   0.0108   0.2832   0.8666
   6.000   0.7579   0.00845   0.00294   0.0107   0.2779   0.8676
   6.250   0.7849   0.00858   0.00306   0.0107   0.2714   0.8687
   6.500   0.8114   0.00872   0.00320   0.0107   0.2650   0.8700
   6.750   0.8379   0.00886   0.00335   0.0108   0.2575   0.8713
   7.000   0.8640   0.00903   0.00352   0.0109   0.2505   0.8725
   7.250   0.8901   0.00920   0.00369   0.0110   0.2423   0.8737
   7.500   0.9158   0.00939   0.00387   0.0111   0.2339   0.8751
   7.750   0.9409   0.00963   0.00408   0.0113   0.2241   0.8765
   8.000   0.9663   0.00983   0.00429   0.0115   0.2147   0.8779
   8.250   0.9909   0.01009   0.00453   0.0118   0.2042   0.8794
   8.500   1.0149   0.01039   0.00479   0.0121   0.1923   0.8809
   8.750   1.0385   0.01070   0.00507   0.0125   0.1810   0.8824
   9.000   1.0613   0.01106   0.00539   0.0131   0.1680   0.8839
   9.250   1.0830   0.01145   0.00574   0.0137   0.1539   0.8856
   9.500   1.1040   0.01186   0.00612   0.0146   0.1400   0.8876
   9.750   1.1237   0.01233   0.00655   0.0155   0.1252   0.8899
  10.000   1.1429   0.01281   0.00699   0.0166   0.1121   0.8924
  10.250   1.1613   0.01331   0.00745   0.0178   0.0998   0.8951
  10.500   1.1795   0.01380   0.00792   0.0189   0.0900   0.8977
  11.000   1.2119   0.01482   0.00893   0.0219   0.0719   0.9034
  11.250   1.2266   0.01530   0.00942   0.0237   0.0657   0.9071
  11.500   1.2353   0.01586   0.00998   0.0265   0.0587   0.9120
  11.750   1.2450   0.01639   0.01054   0.0291   0.0533   0.9171
  12.000   1.2515   0.01703   0.01122   0.0320   0.0479   0.9242
  12.250   1.2580   0.01770   0.01193   0.0347   0.0434   0.9326
  12.750   1.2746   0.01942   0.01379   0.0383   0.0353   0.9642
  13.000   1.2949   0.02097   0.01535   0.0361   0.0282   0.9888
  13.250   1.3024   0.02216   0.01660   0.0372   0.0265   1.0000
  13.500   1.3012   0.02404   0.01848   0.0384   0.0219   1.0000
  13.750   1.3055   0.02570   0.02020   0.0391   0.0205   1.0000
  14.000   1.3096   0.02751   0.02208   0.0394   0.0197   1.0000
  14.250   1.3047   0.03025   0.02484   0.0397   0.0158   1.0000
  14.500   1.3074   0.03242   0.02709   0.0396   0.0156   1.0000
  14.750   1.3027   0.03541   0.03012   0.0394   0.0133   1.0000
  15.000   1.3014   0.03812   0.03292   0.0391   0.0127   1.0000
  15.250   1.2976   0.04117   0.03603   0.0386   0.0119   1.0000
  15.500   1.2896   0.04472   0.03964   0.0380   0.0101   1.0000
  15.750   1.2878   0.04764   0.04266   0.0374   0.0106   1.0000
  16.000   1.2828   0.05095   0.04605   0.0367   0.0102   1.0000
  16.250   1.2766   0.05454   0.04973   0.0358   0.0099   1.0000
  16.500   1.2667   0.05867   0.05393   0.0346   0.0090   1.0000
  16.750   1.2612   0.06237   0.05771   0.0334   0.0086   1.0000
  17.000   1.2548   0.06625   0.06166   0.0322   0.0082   1.0000
  17.250   1.2483   0.07024   0.06573   0.0308   0.0078   1.0000
  17.500   1.2417   0.07431   0.06988   0.0293   0.0076   1.0000
  17.750   1.2312   0.07899   0.07463   0.0276   0.0066   1.0000
  18.000   1.2247   0.08320   0.07891   0.0259   0.0061   1.0000
  18.250   1.2201   0.08721   0.08302   0.0243   0.0065   1.0000
  18.500   1.2129   0.09167   0.08755   0.0224   0.0061   1.0000
  18.750   1.2046   0.09639   0.09234   0.0204   0.0055   1.0000
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