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EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 435 AIRFOIL (e435-il)
Reynolds number: 100,000
Max Cl/Cd: 44.77 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e435-il-100000-n5.txt
Download as CSV file: xf-e435-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 435 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2033   0.07523   0.07019  -0.1124   0.9326   0.0192
  -9.750  -0.2083   0.06811   0.06299  -0.1194   0.9266   0.0189
  -9.500  -0.2229   0.06118   0.05590  -0.1260   0.9181   0.0187
  -9.250  -0.2387   0.05589   0.05040  -0.1303   0.9089   0.0186
  -9.000  -0.2488   0.05194   0.04622  -0.1328   0.9004   0.0184
  -8.750  -0.2633   0.04896   0.04300  -0.1322   0.8893   0.0183
  -8.500  -0.2632   0.04502   0.03864  -0.1337   0.8835   0.0183
  -8.250  -0.2687   0.04262   0.03594  -0.1315   0.8743   0.0183
  -8.000  -0.2583   0.03951   0.03237  -0.1318   0.8693   0.0185
  -7.750  -0.2474   0.03650   0.02876  -0.1313   0.8640   0.0194
  -7.500  -0.2357   0.03539   0.02754  -0.1299   0.8573   0.0200
  -7.250  -0.2126   0.03387   0.02580  -0.1305   0.8537   0.0213
  -7.000  -0.1855   0.03172   0.02320  -0.1313   0.8511   0.0226
  -6.750  -0.1732   0.03047   0.02170  -0.1290   0.8446   0.0233
  -6.500  -0.1518   0.02929   0.02045  -0.1285   0.8400   0.0241
  -6.250  -0.1245   0.02802   0.01904  -0.1288   0.8371   0.0255
  -6.000  -0.0948   0.02676   0.01757  -0.1293   0.8348   0.0276
  -5.750  -0.0832   0.02632   0.01717  -0.1271   0.8283   0.0299
  -5.500  -0.0621   0.02558   0.01635  -0.1264   0.8238   0.0337
  -5.250  -0.0348   0.02468   0.01535  -0.1267   0.8207   0.0383
  -5.000  -0.0050   0.02379   0.01447  -0.1277   0.8184   0.0468
  -4.750   0.0075   0.02345   0.01417  -0.1255   0.8122   0.0561
  -4.500   0.0292   0.02286   0.01363  -0.1250   0.8076   0.0749
  -4.250   0.0579   0.02201   0.01296  -0.1260   0.8046   0.1146
  -4.000   0.0896   0.02079   0.01223  -0.1282   0.8024   0.2156
  -3.750   0.1081   0.01975   0.01224  -0.1281   0.7976   0.4202
  -3.500   0.1242   0.02019   0.01300  -0.1253   0.7921   0.5433
  -3.250   0.1537   0.02051   0.01317  -0.1252   0.7889   0.5918
  -3.000   0.1836   0.02087   0.01339  -0.1248   0.7865   0.6197
  -2.750   0.2104   0.02120   0.01356  -0.1243   0.7833   0.6407
  -2.500   0.2191   0.02182   0.01417  -0.1204   0.7763   0.6539
  -2.250   0.2429   0.02218   0.01444  -0.1190   0.7728   0.6719
  -2.000   0.2697   0.02243   0.01460  -0.1179   0.7703   0.6875
  -1.750   0.3018   0.02244   0.01447  -0.1182   0.7684   0.6977
  -1.500   0.3051   0.02299   0.01501  -0.1143   0.7599   0.7044
  -1.250   0.3361   0.02294   0.01480  -0.1153   0.7566   0.7107
  -1.000   0.3676   0.02283   0.01460  -0.1159   0.7542   0.7145
  -0.750   0.4034   0.02266   0.01430  -0.1175   0.7523   0.7187
  -0.500   0.4096   0.02322   0.01483  -0.1145   0.7438   0.7239
  -0.250   0.4398   0.02318   0.01469  -0.1153   0.7404   0.7275
   0.000   0.4727   0.02304   0.01448  -0.1162   0.7379   0.7306
   0.250   0.5091   0.02287   0.01421  -0.1179   0.7360   0.7339
   0.500   0.5121   0.02354   0.01491  -0.1144   0.7269   0.7380
   0.750   0.5458   0.02348   0.01476  -0.1159   0.7236   0.7422
   1.000   0.5798   0.02331   0.01455  -0.1170   0.7212   0.7450
   1.500   0.6145   0.02392   0.01516  -0.1142   0.7092   0.7516
   1.750   0.6494   0.02377   0.01497  -0.1157   0.7062   0.7554
   2.000   0.6891   0.02354   0.01469  -0.1180   0.7040   0.7593
   2.250   0.6876   0.02430   0.01552  -0.1134   0.6946   0.7628
   2.500   0.7188   0.02421   0.01544  -0.1141   0.6909   0.7661
   2.750   0.7575   0.02395   0.01516  -0.1161   0.6884   0.7695
   3.250   0.7905   0.02458   0.01585  -0.1131   0.6751   0.7779
   3.500   0.8291   0.02426   0.01555  -0.1149   0.6724   0.7815
   3.750   0.8292   0.02501   0.01638  -0.1107   0.6628   0.7864
   4.000   0.8637   0.02481   0.01619  -0.1120   0.6586   0.7906
   4.250   0.9050   0.02438   0.01577  -0.1142   0.6558   0.7941
   4.500   0.9007   0.02528   0.01679  -0.1094   0.6452   0.7991
   4.750   0.9383   0.02488   0.01642  -0.1109   0.6414   0.8040
   5.250   0.9750   0.02535   0.01704  -0.1082   0.6270   0.8145
   5.500   1.0182   0.02470   0.01643  -0.1105   0.6234   0.8195
   5.750   1.0160   0.02569   0.01752  -0.1063   0.6121   0.8259
   6.000   1.0568   0.02500   0.01690  -0.1080   0.6079   0.8312
   6.250   1.0571   0.02594   0.01795  -0.1043   0.5964   0.8393
   6.500   1.0894   0.02549   0.01757  -0.1047   0.5904   0.8460
   6.750   1.0980   0.02609   0.01828  -0.1021   0.5796   0.8551
   7.000   1.1120   0.02639   0.01870  -0.1001   0.5700   0.8642
   7.250   1.1401   0.02610   0.01848  -0.0999   0.5617   0.8740
   7.500   1.1463   0.02675   0.01925  -0.0970   0.5499   0.8883
   7.750   1.1637   0.02680   0.01942  -0.0954   0.5395   0.9077
   8.000   1.1846   0.02646   0.01918  -0.0941   0.5291   0.9717
   8.250   1.2011   0.02713   0.01991  -0.0933   0.5154   1.0000
   8.500   1.2202   0.02769   0.02053  -0.0928   0.5017   1.0000
   8.750   1.2402   0.02817   0.02104  -0.0923   0.4876   1.0000
   9.000   1.2592   0.02870   0.02159  -0.0916   0.4725   1.0000
   9.250   1.2764   0.02933   0.02222  -0.0907   0.4567   1.0000
   9.500   1.2921   0.03004   0.02295  -0.0896   0.4401   1.0000
   9.750   1.3061   0.03087   0.02376  -0.0884   0.4227   1.0000
  10.000   1.3189   0.03180   0.02467  -0.0871   0.4052   1.0000
  10.250   1.3303   0.03284   0.02569  -0.0857   0.3876   1.0000
  10.500   1.3403   0.03401   0.02683  -0.0842   0.3700   1.0000
  10.750   1.3481   0.03536   0.02818  -0.0826   0.3525   1.0000
  11.000   1.3547   0.03685   0.02966  -0.0811   0.3351   1.0000
  11.250   1.3607   0.03843   0.03124  -0.0795   0.3182   1.0000
  11.500   1.3658   0.04013   0.03294  -0.0781   0.3016   1.0000
  11.750   1.3704   0.04192   0.03473  -0.0766   0.2854   1.0000
  12.000   1.3741   0.04384   0.03666  -0.0753   0.2694   1.0000
  12.250   1.3774   0.04587   0.03869  -0.0740   0.2540   1.0000
  12.500   1.3801   0.04801   0.04084  -0.0728   0.2391   1.0000
  12.750   1.3823   0.05028   0.04311  -0.0718   0.2247   1.0000
  13.000   1.3838   0.05268   0.04553  -0.0708   0.2109   1.0000
  13.250   1.3845   0.05523   0.04808  -0.0699   0.1976   1.0000
  13.500   1.3856   0.05785   0.05074  -0.0692   0.1848   1.0000
  13.750   1.3866   0.06056   0.05351  -0.0686   0.1724   1.0000
  14.000   1.3870   0.06340   0.05640  -0.0681   0.1608   1.0000
  14.250   1.3867   0.06641   0.05944  -0.0677   0.1502   1.0000
  14.750   1.3850   0.07279   0.06594  -0.0673   0.1302   1.0000
  15.000   1.3840   0.07612   0.06934  -0.0674   0.1213   1.0000
  15.250   1.3805   0.07982   0.07305  -0.0675   0.1134   1.0000
  15.500   1.3801   0.08327   0.07662  -0.0678   0.1052   1.0000
  15.750   1.3770   0.08709   0.08049  -0.0683   0.0984   1.0000
  16.000   1.3747   0.09091   0.08442  -0.0689   0.0916   1.0000
  16.250   1.3716   0.09487   0.08844  -0.0696   0.0858   1.0000
  16.500   1.3688   0.09889   0.09257  -0.0705   0.0801   1.0000
  16.750   1.3650   0.10307   0.09680  -0.0716   0.0753   1.0000
  17.000   1.3627   0.10715   0.10104  -0.0727   0.0703   1.0000
  17.500   1.3563   0.11562   0.10970  -0.0754   0.0620   1.0000
  17.750   1.3523   0.12006   0.11422  -0.0771   0.0586   1.0000
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