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EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 657 AIRFOIL (e657-il)
Reynolds number: 100,000
Max Cl/Cd: 35.32 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e657-il-100000-n5.txt
Download as CSV file: xf-e657-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 657 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0871   0.10027   0.09463  -0.1167   0.8812   0.0229
 -11.250  -0.0823   0.09642   0.09075  -0.1189   0.8777   0.0227
 -11.000  -0.0774   0.09308   0.08740  -0.1206   0.8740   0.0222
 -10.750  -0.0775   0.08903   0.08338  -0.1224   0.8697   0.0220
 -10.500  -0.0783   0.08474   0.07910  -0.1245   0.8656   0.0218
 -10.250  -0.0801   0.08007   0.07444  -0.1272   0.8620   0.0217
  -9.750  -0.1455   0.05805   0.05234  -0.1415   0.8520   0.0193
  -9.500  -0.1652   0.05367   0.04782  -0.1438   0.8473   0.0192
  -9.250  -0.1835   0.05031   0.04427  -0.1438   0.8433   0.0191
  -9.000  -0.2056   0.04816   0.04197  -0.1411   0.8381   0.0190
  -8.750  -0.2175   0.04588   0.03947  -0.1388   0.8334   0.0190
  -8.500  -0.2275   0.04305   0.03626  -0.1365   0.8296   0.0191
  -8.250  -0.2303   0.04020   0.03291  -0.1344   0.8268   0.0194
  -8.000  -0.2195   0.03963   0.03239  -0.1331   0.8239   0.0203
  -7.750  -0.2151   0.03817   0.03069  -0.1309   0.8202   0.0207
  -7.500  -0.2070   0.03659   0.02880  -0.1290   0.8168   0.0217
  -7.250  -0.1951   0.03461   0.02637  -0.1274   0.8139   0.0225
  -7.000  -0.1781   0.03275   0.02411  -0.1263   0.8117   0.0234
  -6.750  -0.1575   0.03144   0.02263  -0.1257   0.8100   0.0242
  -6.500  -0.1430   0.03053   0.02157  -0.1240   0.8072   0.0250
  -6.250  -0.1309   0.02974   0.02062  -0.1217   0.8035   0.0262
  -6.000  -0.1139   0.02885   0.01954  -0.1201   0.8003   0.0275
  -5.750  -0.0943   0.02823   0.01889  -0.1192   0.7978   0.0300
  -5.500  -0.0729   0.02750   0.01806  -0.1185   0.7958   0.0336
  -5.250  -0.0502   0.02675   0.01718  -0.1178   0.7942   0.0376
  -5.000  -0.0261   0.02607   0.01644  -0.1175   0.7927   0.0439
  -4.750  -0.0241   0.02623   0.01667  -0.1137   0.7871   0.0489
  -4.500  -0.0085   0.02594   0.01636  -0.1121   0.7837   0.0592
  -4.250   0.0114   0.02550   0.01600  -0.1112   0.7813   0.0759
  -4.000   0.0348   0.02497   0.01556  -0.1108   0.7792   0.1041
  -3.750   0.0603   0.02439   0.01516  -0.1108   0.7775   0.1483
  -3.500   0.0870   0.02381   0.01483  -0.1111   0.7761   0.2132
  -3.250   0.0816   0.02448   0.01569  -0.1064   0.7691   0.2515
  -3.000   0.0997   0.02418   0.01573  -0.1053   0.7659   0.3399
  -2.750   0.1215   0.02368   0.01571  -0.1046   0.7636   0.4619
  -2.500   0.1410   0.02340   0.01595  -0.1025   0.7617   0.5923
  -2.250   0.1609   0.02350   0.01625  -0.0998   0.7601   0.6826
  -2.000   0.1509   0.02461   0.01743  -0.0938   0.7521   0.7197
  -1.750   0.1630   0.02506   0.01789  -0.0903   0.7484   0.7572
  -1.500   0.1841   0.02534   0.01806  -0.0884   0.7461   0.7913
  -1.250   0.2099   0.02550   0.01806  -0.0875   0.7444   0.8213
  -1.000   0.1959   0.02658   0.01915  -0.0810   0.7358   0.8395
  -0.750   0.2077   0.02690   0.01941  -0.0777   0.7317   0.8583
  -0.500   0.2278   0.02694   0.01935  -0.0756   0.7294   0.8773
  -0.250   0.2520   0.02687   0.01917  -0.0742   0.7278   0.8953
   0.000   0.2735   0.02688   0.01909  -0.0725   0.7256   0.9136
   0.500   0.2986   0.02804   0.02018  -0.0685   0.7131   0.9517
   0.750   0.3460   0.02801   0.02004  -0.0721   0.7120   0.9652
   1.000   0.3942   0.02794   0.01986  -0.0759   0.7110   0.9738
   1.250   0.4397   0.02784   0.01965  -0.0794   0.7098   0.9801
   1.750   0.4738   0.02911   0.02087  -0.0788   0.6961   1.0000
   2.000   0.5025   0.02886   0.02054  -0.0789   0.6944   1.0000
   2.500   0.5167   0.02999   0.02161  -0.0741   0.6800   1.0000
   2.750   0.5442   0.03003   0.02159  -0.0744   0.6769   1.0000
   3.250   0.5808   0.03091   0.02243  -0.0730   0.6644   1.0000
   3.500   0.6117   0.03082   0.02232  -0.0737   0.6616   1.0000
   3.750   0.6171   0.03193   0.02344  -0.0718   0.6508   1.0000
   4.000   0.6513   0.03164   0.02313  -0.0727   0.6486   1.0000
   4.500   0.6897   0.03255   0.02405  -0.0716   0.6347   1.0000
   4.750   0.7247   0.03211   0.02363  -0.0725   0.6327   1.0000
   5.250   0.7646   0.03284   0.02440  -0.0714   0.6183   1.0000
   5.750   0.8060   0.03344   0.02508  -0.0704   0.6039   1.0000
   6.000   0.8394   0.03285   0.02453  -0.0709   0.6013   1.0000
   6.500   0.8664   0.03434   0.02612  -0.0686   0.5805   1.0000
   6.750   0.8932   0.03411   0.02594  -0.0684   0.5746   1.0000
   7.000   0.9285   0.03325   0.02513  -0.0689   0.5715   1.0000
   7.500   0.9762   0.03319   0.02521  -0.0681   0.5556   1.0000
   7.750   0.9887   0.03404   0.02612  -0.0669   0.5429   1.0000
   8.000   1.0078   0.03440   0.02656  -0.0662   0.5320   1.0000
   8.250   1.0427   0.03349   0.02571  -0.0665   0.5253   1.0000
   8.500   1.0610   0.03391   0.02619  -0.0657   0.5123   1.0000
   8.750   1.0847   0.03392   0.02627  -0.0652   0.5003   1.0000
   9.000   1.1131   0.03356   0.02594  -0.0650   0.4881   1.0000
   9.250   1.1409   0.03325   0.02566  -0.0648   0.4745   1.0000
   9.500   1.1648   0.03327   0.02569  -0.0643   0.4590   1.0000
   9.750   1.1852   0.03358   0.02600  -0.0636   0.4422   1.0000
  10.000   1.2033   0.03407   0.02650  -0.0627   0.4245   1.0000
  10.250   1.2196   0.03471   0.02714  -0.0617   0.4064   1.0000
  10.500   1.2341   0.03551   0.02792  -0.0606   0.3880   1.0000
  10.750   1.2470   0.03644   0.02883  -0.0594   0.3697   1.0000
  11.000   1.2582   0.03752   0.02988  -0.0582   0.3516   1.0000
  11.250   1.2680   0.03874   0.03107  -0.0569   0.3338   1.0000
  11.500   1.2764   0.04010   0.03241  -0.0556   0.3165   1.0000
  11.750   1.2836   0.04161   0.03391  -0.0544   0.2996   1.0000
  12.000   1.2905   0.04319   0.03550  -0.0532   0.2833   1.0000
  12.250   1.2965   0.04490   0.03721  -0.0520   0.2675   1.0000
  12.500   1.3019   0.04670   0.03903  -0.0509   0.2521   1.0000
  12.750   1.3066   0.04862   0.04094  -0.0498   0.2373   1.0000
  13.000   1.3109   0.05063   0.04296  -0.0489   0.2232   1.0000
  13.250   1.3147   0.05277   0.04514  -0.0480   0.2094   1.0000
  13.500   1.3186   0.05496   0.04737  -0.0472   0.1963   1.0000
  13.750   1.3217   0.05728   0.04975  -0.0465   0.1839   1.0000
  14.000   1.3244   0.05971   0.05222  -0.0459   0.1722   1.0000
  14.250   1.3258   0.06233   0.05485  -0.0454   0.1612   1.0000
  14.500   1.3271   0.06504   0.05761  -0.0449   0.1505   1.0000
  14.750   1.3290   0.06777   0.06043  -0.0447   0.1403   1.0000
  15.000   1.3294   0.07073   0.06343  -0.0445   0.1312   1.0000
  15.250   1.3287   0.07389   0.06663  -0.0444   0.1226   1.0000
  15.500   1.3296   0.07694   0.06981  -0.0444   0.1142   1.0000
  15.750   1.3275   0.08040   0.07329  -0.0446   0.1072   1.0000
  16.000   1.3273   0.08375   0.07677  -0.0450   0.0997   1.0000
  16.250   1.3251   0.08740   0.08047  -0.0454   0.0935   1.0000
  16.500   1.3235   0.09107   0.08427  -0.0460   0.0872   1.0000
  16.750   1.3207   0.09492   0.08817  -0.0468   0.0821   1.0000
  17.000   1.3186   0.09877   0.09217  -0.0477   0.0766   1.0000
  17.250   1.3144   0.10293   0.09635  -0.0488   0.0725   1.0000
  17.500   1.3130   0.10682   0.10043  -0.0499   0.0677   1.0000
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