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EPPLER 360 AIRFOIL (e360-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 360 AIRFOIL (e360-il)
Reynolds number: 500,000
Max Cl/Cd: 69.05 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e360-il-500000-n5.txt
Download as CSV file: xf-e360-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 360 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6674   0.06599   0.06346  -0.0392   1.0000   0.0062
 -11.500  -0.7022   0.05534   0.05253  -0.0469   1.0000   0.0061
 -11.250  -0.7318   0.04939   0.04642  -0.0487   1.0000   0.0060
 -11.000  -0.7533   0.04540   0.04227  -0.0480   1.0000   0.0059
 -10.750  -0.7766   0.04140   0.03799  -0.0454   1.0000   0.0060
 -10.500  -0.7930   0.03862   0.03501  -0.0417   1.0000   0.0059
 -10.250  -0.8123   0.03569   0.03177  -0.0363   1.0000   0.0060
 -10.000  -0.8170   0.03336   0.02919  -0.0326   1.0000   0.0060
  -9.750  -0.8154   0.03145   0.02704  -0.0293   1.0000   0.0060
  -9.500  -0.8137   0.02932   0.02463  -0.0259   1.0000   0.0061
  -9.250  -0.8083   0.02743   0.02248  -0.0228   1.0000   0.0061
  -9.000  -0.7995   0.02586   0.02069  -0.0200   1.0000   0.0061
  -8.750  -0.7889   0.02442   0.01905  -0.0174   1.0000   0.0061
  -8.500  -0.7631   0.02279   0.01719  -0.0179   0.9954   0.0061
  -8.250  -0.7365   0.02111   0.01531  -0.0184   0.9881   0.0061
  -8.000  -0.7089   0.01974   0.01377  -0.0190   0.9794   0.0062
  -7.750  -0.6803   0.01849   0.01237  -0.0198   0.9675   0.0063
  -7.500  -0.6473   0.01739   0.01117  -0.0213   0.9507   0.0064
  -7.250  -0.6084   0.01636   0.01004  -0.0241   0.9311   0.0065
  -7.000  -0.5732   0.01554   0.00909  -0.0259   0.9043   0.0066
  -6.750  -0.5472   0.01497   0.00837  -0.0257   0.8757   0.0069
  -6.250  -0.5027   0.01406   0.00718  -0.0235   0.8289   0.0072
  -6.000  -0.4804   0.01364   0.00664  -0.0224   0.8098   0.0075
  -5.750  -0.4578   0.01324   0.00612  -0.0214   0.7935   0.0079
  -5.500  -0.4346   0.01290   0.00568  -0.0204   0.7786   0.0082
  -5.250  -0.4116   0.01252   0.00521  -0.0195   0.7648   0.0088
  -5.000  -0.3878   0.01222   0.00483  -0.0187   0.7518   0.0094
  -4.750  -0.3635   0.01195   0.00449  -0.0179   0.7397   0.0104
  -4.500  -0.3393   0.01166   0.00414  -0.0172   0.7282   0.0120
  -4.250  -0.3146   0.01143   0.00385  -0.0166   0.7174   0.0142
  -4.000  -0.2902   0.01117   0.00357  -0.0159   0.7069   0.0197
  -3.750  -0.2656   0.01089   0.00333  -0.0153   0.6974   0.0305
  -3.500  -0.2410   0.01065   0.00311  -0.0146   0.6883   0.0459
  -3.250  -0.2161   0.01040   0.00291  -0.0141   0.6791   0.0639
  -3.000  -0.1919   0.01012   0.00272  -0.0135   0.6711   0.0960
  -2.750  -0.1689   0.00968   0.00251  -0.0127   0.6629   0.1583
  -2.500  -0.1479   0.00910   0.00229  -0.0116   0.6555   0.2606
  -2.250  -0.1279   0.00845   0.00207  -0.0104   0.6479   0.3823
  -2.000  -0.1090   0.00781   0.00187  -0.0088   0.6412   0.5104
  -1.750  -0.0886   0.00735   0.00179  -0.0073   0.6343   0.6153
  -1.500  -0.0652   0.00716   0.00177  -0.0063   0.6276   0.6775
  -1.250  -0.0399   0.00708   0.00178  -0.0056   0.6214   0.7176
  -1.000  -0.0143   0.00705   0.00181  -0.0049   0.6148   0.7528
  -0.750   0.0116   0.00707   0.00185  -0.0042   0.6089   0.7779
  -0.500   0.0384   0.00709   0.00188  -0.0038   0.6026   0.7947
  -0.250   0.0653   0.00713   0.00189  -0.0034   0.5964   0.8070
   0.000   0.0925   0.00716   0.00190  -0.0032   0.5905   0.8172
   0.250   0.1200   0.00719   0.00192  -0.0029   0.5838   0.8242
   0.500   0.1473   0.00724   0.00191  -0.0028   0.5763   0.8303
   0.750   0.1748   0.00727   0.00191  -0.0026   0.5660   0.8348
   1.000   0.2021   0.00731   0.00191  -0.0024   0.5541   0.8392
   1.250   0.2292   0.00737   0.00191  -0.0022   0.5406   0.8440
   1.500   0.2562   0.00743   0.00191  -0.0020   0.5267   0.8487
   1.750   0.2833   0.00749   0.00194  -0.0018   0.5140   0.8527
   2.000   0.3106   0.00755   0.00197  -0.0016   0.5030   0.8571
   2.250   0.3377   0.00761   0.00201  -0.0015   0.4907   0.8619
   2.500   0.3647   0.00769   0.00205  -0.0013   0.4773   0.8661
   2.750   0.3915   0.00777   0.00211  -0.0010   0.4629   0.8703
   3.000   0.4177   0.00789   0.00218  -0.0007   0.4431   0.8752
   3.250   0.4435   0.00805   0.00224  -0.0003   0.4202   0.8802
   3.500   0.4689   0.00823   0.00235   0.0001   0.3939   0.8845
   3.750   0.4933   0.00848   0.00249   0.0007   0.3595   0.8896
   4.000   0.5163   0.00885   0.00267   0.0014   0.3150   0.8952
   4.250   0.5398   0.00920   0.00287   0.0021   0.2779   0.9002
   4.500   0.5634   0.00953   0.00309   0.0028   0.2475   0.9060
   4.750   0.5870   0.00985   0.00331   0.0034   0.2211   0.9121
   5.250   0.6350   0.01047   0.00377   0.0046   0.1779   0.9244
   5.500   0.6598   0.01074   0.00401   0.0050   0.1638   0.9307
   5.750   0.6852   0.01102   0.00426   0.0053   0.1511   0.9373
   6.000   0.7105   0.01131   0.00450   0.0056   0.1396   0.9445
   6.250   0.7386   0.01158   0.00478   0.0052   0.1310   0.9505
   6.500   0.7654   0.01189   0.00506   0.0052   0.1232   0.9578
   6.750   0.7957   0.01217   0.00535   0.0043   0.1162   0.9629
   7.000   0.8247   0.01251   0.00568   0.0037   0.1095   0.9691
   7.250   0.8548   0.01279   0.00598   0.0028   0.1044   0.9744
   7.500   0.8852   0.01316   0.00633   0.0018   0.0987   0.9793
   7.750   0.9147   0.01348   0.00668   0.0010   0.0948   0.9849
   8.000   0.9466   0.01381   0.00703  -0.0003   0.0902   0.9884
   8.250   0.9763   0.01422   0.00744  -0.0013   0.0855   0.9931
   8.500   1.0067   0.01458   0.00783  -0.0023   0.0822   0.9981
   8.750   1.0294   0.01491   0.00819  -0.0018   0.0790   1.0000
   9.000   1.0448   0.01524   0.00853   0.0003   0.0757   1.0000
   9.250   1.0601   0.01564   0.00892   0.0023   0.0724   1.0000
   9.500   1.0777   0.01595   0.00929   0.0039   0.0703   1.0000
   9.750   1.0949   0.01631   0.00969   0.0055   0.0676   1.0000
  10.000   1.1113   0.01674   0.01012   0.0072   0.0645   1.0000
  10.250   1.1267   0.01721   0.01061   0.0090   0.0618   1.0000
  10.500   1.1428   0.01760   0.01107   0.0107   0.0599   1.0000
  10.750   1.1564   0.01803   0.01154   0.0128   0.0575   1.0000
  11.000   1.1690   0.01854   0.01207   0.0150   0.0549   1.0000
  11.250   1.1804   0.01915   0.01269   0.0172   0.0524   1.0000
  11.500   1.1943   0.01967   0.01329   0.0189   0.0509   1.0000
  11.750   1.2074   0.02027   0.01394   0.0206   0.0486   1.0000
  12.000   1.2190   0.02098   0.01468   0.0223   0.0462   1.0000
  12.250   1.2290   0.02184   0.01556   0.0240   0.0439   1.0000
  12.500   1.2412   0.02261   0.01641   0.0254   0.0424   1.0000
  12.750   1.2523   0.02349   0.01736   0.0267   0.0409   1.0000
  13.000   1.2622   0.02450   0.01843   0.0280   0.0390   1.0000
  13.250   1.2705   0.02569   0.01966   0.0292   0.0374   1.0000
  13.500   1.2791   0.02691   0.02095   0.0302   0.0360   1.0000
  13.750   1.2888   0.02811   0.02223   0.0310   0.0346   1.0000
  14.000   1.2970   0.02946   0.02366   0.0318   0.0331   1.0000
  14.250   1.3037   0.03101   0.02527   0.0324   0.0320   1.0000
  14.500   1.3084   0.03279   0.02711   0.0330   0.0306   1.0000
  14.750   1.3143   0.03452   0.02892   0.0334   0.0295   1.0000
  15.000   1.3201   0.03631   0.03083   0.0337   0.0286   1.0000
  15.250   1.3247   0.03826   0.03286   0.0339   0.0274   1.0000
  15.500   1.3276   0.04043   0.03511   0.0339   0.0265   1.0000
  15.750   1.3280   0.04292   0.03766   0.0338   0.0252   1.0000
  16.000   1.3280   0.04552   0.04035   0.0336   0.0245   1.0000
  16.250   1.3289   0.04809   0.04304   0.0333   0.0237   1.0000
  16.500   1.3287   0.05088   0.04593   0.0327   0.0229   1.0000
  16.750   1.3262   0.05401   0.04917   0.0320   0.0223   1.0000
  17.000   1.3226   0.05742   0.05267   0.0310   0.0215   1.0000
  17.250   1.3168   0.06125   0.05659   0.0298   0.0209   1.0000
  17.500   1.3084   0.06557   0.06101   0.0282   0.0203   1.0000
  17.750   1.3016   0.06983   0.06540   0.0265   0.0197   1.0000
  18.000   1.2935   0.07443   0.07013   0.0245   0.0193   1.0000
  18.250   1.2833   0.07949   0.07532   0.0222   0.0189   1.0000
  18.500   1.2716   0.08494   0.08090   0.0197   0.0185   1.0000
  18.750   1.2569   0.09111   0.08720   0.0166   0.0181   1.0000
  19.000   1.2399   0.09783   0.09405   0.0131   0.0178   1.0000
  19.250   1.2207   0.10513   0.10149   0.0093   0.0176   1.0000
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