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EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 655 AIRFOIL (e655-il)
Reynolds number: 100,000
Max Cl/Cd: 30.74 at α=10.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e655-il-100000-n5.txt
Download as CSV file: xf-e655-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 655 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.2334   0.09821   0.09293  -0.0988   0.8934   0.0252
 -12.500  -0.2658   0.08484   0.07952  -0.1062   0.8862   0.0251
 -12.250  -0.2998   0.07228   0.06681  -0.1153   0.8781   0.0244
 -12.000  -0.3330   0.06274   0.05701  -0.1229   0.8684   0.0238
 -11.750  -0.3601   0.05615   0.05010  -0.1275   0.8596   0.0237
 -11.500  -0.3791   0.05180   0.04549  -0.1292   0.8506   0.0236
 -11.250  -0.3947   0.04807   0.04145  -0.1299   0.8436   0.0238
 -11.000  -0.4072   0.04504   0.03814  -0.1293   0.8365   0.0240
 -10.750  -0.4166   0.04235   0.03511  -0.1281   0.8302   0.0246
 -10.500  -0.4219   0.03993   0.03230  -0.1265   0.8251   0.0251
 -10.250  -0.4209   0.03859   0.03085  -0.1247   0.8192   0.0260
 -10.000  -0.4156   0.03752   0.02967  -0.1230   0.8142   0.0270
  -9.750  -0.4070   0.03611   0.02803  -0.1217   0.8103   0.0282
  -9.500  -0.3976   0.03446   0.02606  -0.1202   0.8060   0.0295
  -9.250  -0.3846   0.03302   0.02446  -0.1189   0.8019   0.0308
  -9.000  -0.3695   0.03194   0.02328  -0.1179   0.7984   0.0321
  -8.750  -0.3529   0.03088   0.02201  -0.1169   0.7953   0.0345
  -8.500  -0.3353   0.02985   0.02086  -0.1161   0.7926   0.0370
  -8.250  -0.3198   0.02908   0.02002  -0.1149   0.7888   0.0398
  -8.000  -0.3029   0.02820   0.01904  -0.1137   0.7850   0.0430
  -7.750  -0.2857   0.02752   0.01831  -0.1126   0.7817   0.0470
  -7.500  -0.2673   0.02673   0.01744  -0.1116   0.7789   0.0514
  -7.250  -0.2476   0.02608   0.01669  -0.1108   0.7767   0.0572
  -7.000  -0.2301   0.02546   0.01607  -0.1097   0.7740   0.0630
  -6.750  -0.2141   0.02495   0.01554  -0.1083   0.7705   0.0704
  -6.500  -0.1960   0.02448   0.01503  -0.1071   0.7672   0.0796
  -6.250  -0.1773   0.02395   0.01451  -0.1061   0.7642   0.0910
  -6.000  -0.1571   0.02344   0.01401  -0.1053   0.7617   0.1058
  -5.750  -0.1364   0.02291   0.01355  -0.1046   0.7598   0.1250
  -5.500  -0.1164   0.02253   0.01323  -0.1038   0.7575   0.1496
  -5.250  -0.1006   0.02228   0.01313  -0.1024   0.7539   0.1771
  -5.000  -0.0825   0.02197   0.01296  -0.1013   0.7506   0.2126
  -4.750  -0.0628   0.02160   0.01274  -0.1004   0.7477   0.2562
  -4.500  -0.0419   0.02119   0.01253  -0.0997   0.7454   0.3100
  -4.250  -0.0203   0.02078   0.01235  -0.0991   0.7436   0.3733
  -4.000   0.0022   0.02040   0.01225  -0.0983   0.7419   0.4467
  -3.750   0.0149   0.02056   0.01274  -0.0958   0.7378   0.5126
  -3.500   0.0315   0.02087   0.01329  -0.0934   0.7342   0.5730
  -3.250   0.0523   0.02122   0.01367  -0.0918   0.7315   0.6197
  -3.000   0.0757   0.02153   0.01390  -0.0907   0.7293   0.6531
  -2.750   0.1007   0.02182   0.01410  -0.0897   0.7273   0.6776
  -2.500   0.1274   0.02206   0.01420  -0.0892   0.7256   0.6990
  -2.250   0.1399   0.02269   0.01482  -0.0866   0.7213   0.7147
  -2.000   0.1543   0.02325   0.01535  -0.0843   0.7173   0.7289
  -1.750   0.1746   0.02360   0.01563  -0.0828   0.7143   0.7426
  -1.500   0.1987   0.02382   0.01575  -0.0819   0.7119   0.7562
  -1.250   0.2232   0.02402   0.01587  -0.0808   0.7101   0.7670
  -1.000   0.2492   0.02417   0.01594  -0.0801   0.7086   0.7775
  -0.750   0.2463   0.02514   0.01694  -0.0759   0.7013   0.7892
  -0.500   0.2622   0.02549   0.01728  -0.0735   0.6978   0.7978
  -0.250   0.2858   0.02564   0.01735  -0.0728   0.6954   0.8079
   0.000   0.3112   0.02569   0.01733  -0.0720   0.6935   0.8161
   0.250   0.3402   0.02567   0.01723  -0.0720   0.6920   0.8245
   0.750   0.3465   0.02706   0.01867  -0.0651   0.6795   0.8413
   1.000   0.3735   0.02701   0.01857  -0.0647   0.6776   0.8474
   1.250   0.4055   0.02692   0.01840  -0.0655   0.6761   0.8538
   1.750   0.4101   0.02831   0.01984  -0.0587   0.6626   0.8680
   2.000   0.4420   0.02815   0.01964  -0.0593   0.6608   0.8728
   2.250   0.4754   0.02793   0.01938  -0.0601   0.6594   0.8771
   2.750   0.4817   0.02939   0.02089  -0.0539   0.6451   0.8917
   3.000   0.5160   0.02907   0.02054  -0.0548   0.6437   0.8962
   3.500   0.5306   0.03069   0.02222  -0.0505   0.6292   0.9114
   3.750   0.5276   0.03223   0.02381  -0.0479   0.6185   0.9205
   4.000   0.5548   0.03215   0.02374  -0.0479   0.6151   0.9271
   4.250   0.5879   0.03176   0.02336  -0.0485   0.6132   0.9331
   4.500   0.6237   0.03123   0.02285  -0.0494   0.6118   0.9386
   5.000   0.6605   0.03254   0.02427  -0.0492   0.5973   0.9595
   5.250   0.7019   0.03189   0.02366  -0.0511   0.5960   0.9682
   5.750   0.7430   0.03301   0.02487  -0.0518   0.5812   1.0000
   6.250   0.7828   0.03411   0.02604  -0.0520   0.5666   1.0000
   6.750   0.8244   0.03502   0.02704  -0.0520   0.5520   1.0000
   7.000   0.8622   0.03413   0.02619  -0.0530   0.5500   1.0000
   8.000   0.9491   0.03529   0.02756  -0.0525   0.5190   1.0000
   8.500   0.9732   0.03740   0.02979  -0.0511   0.4958   1.0000
   8.750   1.0073   0.03656   0.02900  -0.0514   0.4900   1.0000
   9.000   1.0215   0.03745   0.02996  -0.0507   0.4780   1.0000
   9.250   1.0492   0.03715   0.02970  -0.0507   0.4691   1.0000
   9.500   1.0764   0.03689   0.02947  -0.0505   0.4589   1.0000
   9.750   1.0942   0.03745   0.03009  -0.0500   0.4461   1.0000
  10.000   1.1163   0.03763   0.03029  -0.0496   0.4334   1.0000
  10.250   1.1396   0.03770   0.03036  -0.0492   0.4203   1.0000
  10.500   1.1614   0.03792   0.03057  -0.0487   0.4063   1.0000
  10.750   1.1801   0.03839   0.03103  -0.0481   0.3913   1.0000
  11.000   1.1959   0.03911   0.03173  -0.0473   0.3758   1.0000
  11.250   1.2096   0.04004   0.03264  -0.0465   0.3602   1.0000
  11.500   1.2214   0.04114   0.03372  -0.0456   0.3447   1.0000
  11.750   1.2315   0.04241   0.03498  -0.0447   0.3293   1.0000
  12.000   1.2407   0.04379   0.03634  -0.0438   0.3144   1.0000
  12.500   1.2549   0.04706   0.03960  -0.0421   0.2850   1.0000
  12.750   1.2609   0.04887   0.04142  -0.0413   0.2710   1.0000
  13.000   1.2664   0.05078   0.04336  -0.0406   0.2574   1.0000
  13.250   1.2718   0.05275   0.04534  -0.0400   0.2444   1.0000
  13.500   1.2765   0.05482   0.04742  -0.0394   0.2319   1.0000
  13.750   1.2808   0.05698   0.04957  -0.0389   0.2199   1.0000
  14.000   1.2839   0.05932   0.05192  -0.0384   0.2081   1.0000
  14.250   1.2872   0.06175   0.05441  -0.0381   0.1966   1.0000
  14.500   1.2901   0.06425   0.05696  -0.0378   0.1861   1.0000
  14.750   1.2920   0.06687   0.05958  -0.0376   0.1761   1.0000
  15.000   1.2938   0.06963   0.06241  -0.0376   0.1661   1.0000
  15.250   1.2954   0.07247   0.06531  -0.0376   0.1568   1.0000
  15.500   1.2955   0.07549   0.06831  -0.0377   0.1485   1.0000
  15.750   1.2968   0.07854   0.07148  -0.0380   0.1397   1.0000
  16.000   1.2967   0.08174   0.07472  -0.0383   0.1321   1.0000
  16.250   1.2962   0.08507   0.07814  -0.0388   0.1245   1.0000
  16.500   1.2959   0.08844   0.08157  -0.0393   0.1177   1.0000
  16.750   1.2945   0.09202   0.08524  -0.0400   0.1112   1.0000
  17.000   1.2938   0.09555   0.08883  -0.0408   0.1051   1.0000
  17.250   1.2921   0.09929   0.09267  -0.0418   0.0994   1.0000
  17.500   1.2903   0.10304   0.09644  -0.0428   0.0943   1.0000
  17.750   1.2888   0.10689   0.10045  -0.0440   0.0889   1.0000
  18.000   1.2859   0.11084   0.10440  -0.0453   0.0846   1.0000
  18.500   1.2821   0.11884   0.11266  -0.0483   0.0758   1.0000
  18.750   1.2803   0.12273   0.11655  -0.0499   0.0723   1.0000
  19.000   1.2781   0.12691   0.12091  -0.0517   0.0684   1.0000
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