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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 500,000
Max Cl/Cd: 112.21 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e432-il-500000.txt
Download as CSV file: xf-e432-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 432 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2063   0.11785   0.11560  -0.0643   0.9905   0.0161
 -11.500  -0.1949   0.11267   0.11043  -0.0690   0.9853   0.0170
 -11.250  -0.1965   0.10476   0.10252  -0.0757   0.9735   0.0176
 -10.750  -0.1639   0.09654   0.09428  -0.0836   0.9458   0.0182
 -10.500  -0.1346   0.09169   0.08938  -0.0916   0.9350   0.0190
 -10.250  -0.0236   0.06967   0.06682  -0.1100   0.8167   0.0222
 -10.000  -0.0226   0.06640   0.06350  -0.1108   0.8027   0.0225
  -9.750  -0.0243   0.06253   0.05958  -0.1120   0.7915   0.0228
  -9.500  -0.0288   0.05819   0.05519  -0.1135   0.7819   0.0233
  -9.250  -0.0370   0.05300   0.04998  -0.1160   0.7735   0.0237
  -9.000  -0.0584   0.04498   0.04192  -0.1220   0.7672   0.0238
  -8.750  -0.0899   0.03840   0.03525  -0.1258   0.7600   0.0232
  -8.500  -0.1163   0.03442   0.03112  -0.1258   0.7522   0.0230
  -8.250  -0.1386   0.03172   0.02830  -0.1234   0.7447   0.0230
  -8.000  -0.1462   0.02912   0.02553  -0.1217   0.7379   0.0239
  -7.750  -0.1775   0.02530   0.02092  -0.1171   0.7316   0.0257
  -7.500  -0.1797   0.03405   0.02941  -0.1225   0.7372   0.0262
  -7.250  -0.1881   0.02586   0.02025  -0.1180   0.7319   0.0179
  -7.000  -0.1670   0.02428   0.01859  -0.1173   0.7258   0.0171
  -6.750  -0.1526   0.02042   0.01398  -0.1151   0.7207   0.0145
  -6.500  -0.1291   0.01912   0.01251  -0.1145   0.7158   0.0142
  -6.250  -0.1060   0.01769   0.01094  -0.1138   0.7106   0.0139
  -6.000  -0.0821   0.01660   0.00970  -0.1132   0.7056   0.0138
  -5.750  -0.0578   0.01573   0.00868  -0.1127   0.7011   0.0138
  -5.500  -0.0336   0.01498   0.00786  -0.1121   0.6967   0.0139
  -5.250  -0.0093   0.01435   0.00715  -0.1115   0.6922   0.0141
  -5.000   0.0143   0.01368   0.00642  -0.1110   0.6879   0.0145
  -4.750   0.0386   0.01314   0.00582  -0.1106   0.6837   0.0153
  -4.500   0.0637   0.01272   0.00540  -0.1103   0.6797   0.0165
  -4.250   0.0891   0.01229   0.00493  -0.1100   0.6757   0.0181
  -4.000   0.1150   0.01190   0.00453  -0.1098   0.6718   0.0227
  -3.750   0.1414   0.01155   0.00416  -0.1097   0.6679   0.0349
  -3.500   0.1671   0.01112   0.00391  -0.1096   0.6642   0.0668
  -3.250   0.1934   0.01075   0.00373  -0.1097   0.6605   0.1146
  -3.000   0.2194   0.01024   0.00354  -0.1099   0.6568   0.2013
  -2.750   0.2450   0.00940   0.00330  -0.1105   0.6533   0.3837
  -2.500   0.2700   0.00852   0.00334  -0.1108   0.6498   0.6490
  -2.250   0.2977   0.00859   0.00345  -0.1106   0.6462   0.6958
  -2.000   0.3257   0.00870   0.00354  -0.1105   0.6425   0.7164
  -1.750   0.3538   0.00883   0.00361  -0.1104   0.6390   0.7322
  -1.500   0.3823   0.00904   0.00372  -0.1104   0.6356   0.7461
  -1.250   0.4094   0.00918   0.00386  -0.1101   0.6323   0.7560
  -1.000   0.4371   0.00927   0.00392  -0.1100   0.6287   0.7640
  -0.750   0.4642   0.00940   0.00403  -0.1097   0.6251   0.7716
  -0.500   0.4916   0.00954   0.00412  -0.1095   0.6218   0.7804
  -0.250   0.5180   0.00983   0.00437  -0.1089   0.6185   0.7914
   0.000   0.5428   0.00994   0.00452  -0.1080   0.6152   0.7993
   0.250   0.5695   0.01003   0.00460  -0.1077   0.6115   0.8047
   0.500   0.5983   0.01007   0.00459  -0.1081   0.6080   0.8083
   0.750   0.6277   0.01012   0.00457  -0.1087   0.6047   0.8110
   1.000   0.6556   0.01018   0.00459  -0.1088   0.6013   0.8130
   1.250   0.6827   0.01018   0.00462  -0.1088   0.5977   0.8150
   1.500   0.7104   0.01021   0.00463  -0.1089   0.5940   0.8172
   1.750   0.7385   0.01024   0.00464  -0.1091   0.5904   0.8195
   2.000   0.7677   0.01034   0.00467  -0.1096   0.5870   0.8217
   2.250   0.7958   0.01037   0.00472  -0.1099   0.5833   0.8241
   2.500   0.8241   0.01041   0.00475  -0.1103   0.5792   0.8266
   2.750   0.8513   0.01041   0.00476  -0.1103   0.5753   0.8285
   3.000   0.8790   0.01048   0.00479  -0.1105   0.5715   0.8303
   3.250   0.9058   0.01053   0.00487  -0.1105   0.5674   0.8323
   3.500   0.9325   0.01056   0.00493  -0.1104   0.5629   0.8345
   3.750   0.9597   0.01060   0.00497  -0.1105   0.5585   0.8369
   4.000   0.9881   0.01073   0.00503  -0.1109   0.5543   0.8396
   4.250   1.0146   0.01075   0.00512  -0.1109   0.5495   0.8421
   4.500   1.0409   0.01078   0.00518  -0.1108   0.5447   0.8442
   4.750   1.0672   0.01085   0.00523  -0.1107   0.5401   0.8462
   5.000   1.0926   0.01092   0.00535  -0.1105   0.5352   0.8485
   5.250   1.1180   0.01096   0.00545  -0.1103   0.5298   0.8510
   5.500   1.1441   0.01106   0.00553  -0.1102   0.5247   0.8538
   5.750   1.1697   0.01116   0.00566  -0.1100   0.5192   0.8569
   6.000   1.1948   0.01122   0.00577  -0.1098   0.5131   0.8595
   6.250   1.2191   0.01135   0.00588  -0.1093   0.5075   0.8620
   6.500   1.2424   0.01140   0.00603  -0.1087   0.5010   0.8648
   6.750   1.2658   0.01152   0.00617  -0.1081   0.4944   0.8679
   7.000   1.2894   0.01165   0.00634  -0.1076   0.4875   0.8711
   7.250   1.3126   0.01179   0.00650  -0.1070   0.4800   0.8744
   7.500   1.3333   0.01191   0.00668  -0.1059   0.4723   0.8777
   7.750   1.3533   0.01207   0.00687  -0.1047   0.4639   0.8816
   8.000   1.3734   0.01224   0.00709  -0.1035   0.4552   0.8858
   8.250   1.3908   0.01247   0.00730  -0.1019   0.4460   0.8901
   8.500   1.4064   0.01262   0.00753  -0.0998   0.4361   0.8945
   8.750   1.4210   0.01288   0.00782  -0.0976   0.4259   0.8999
   9.000   1.4340   0.01322   0.00816  -0.0953   0.4144   0.9058
   9.250   1.4457   0.01353   0.00852  -0.0926   0.4020   0.9127
   9.500   1.4562   0.01393   0.00894  -0.0899   0.3881   0.9213
   9.750   1.4636   0.01437   0.00940  -0.0867   0.3742   0.9327
  10.000   1.4679   0.01487   0.00993  -0.0830   0.3593   0.9543
  10.250   1.4787   0.01562   0.01066  -0.0813   0.3417   1.0000
  10.750   1.4926   0.01772   0.01264  -0.0769   0.3060   1.0000
  11.000   1.4969   0.01897   0.01384  -0.0746   0.2884   1.0000
  11.250   1.4999   0.02036   0.01518  -0.0723   0.2719   1.0000
  11.500   1.5020   0.02190   0.01668  -0.0701   0.2562   1.0000
  11.750   1.5030   0.02359   0.01834  -0.0680   0.2407   1.0000
  12.000   1.5038   0.02541   0.02012  -0.0661   0.2263   1.0000
  12.250   1.5041   0.02734   0.02202  -0.0643   0.2124   1.0000
  12.500   1.5037   0.02941   0.02406  -0.0626   0.1989   1.0000
  12.750   1.5031   0.03159   0.02622  -0.0611   0.1863   1.0000
  13.000   1.5017   0.03390   0.02850  -0.0597   0.1741   1.0000
  13.250   1.5019   0.03617   0.03077  -0.0585   0.1625   1.0000
  13.500   1.5032   0.03842   0.03302  -0.0575   0.1520   1.0000
  13.750   1.5023   0.04092   0.03551  -0.0566   0.1413   1.0000
  14.000   1.5010   0.04354   0.03812  -0.0557   0.1317   1.0000
  14.250   1.5001   0.04621   0.04078  -0.0550   0.1218   1.0000
  14.500   1.5001   0.04884   0.04342  -0.0544   0.1123   1.0000
  14.750   1.4989   0.05168   0.04627  -0.0539   0.1037   1.0000
  15.250   1.4972   0.05751   0.05211  -0.0533   0.0875   1.0000
  15.500   1.4960   0.06056   0.05518  -0.0532   0.0806   1.0000
  15.750   1.4935   0.06385   0.05847  -0.0532   0.0738   1.0000
  16.000   1.4937   0.06688   0.06154  -0.0533   0.0673   1.0000
  16.250   1.4908   0.07036   0.06502  -0.0535   0.0612   1.0000
  16.500   1.4901   0.07364   0.06836  -0.0538   0.0567   1.0000
  16.750   1.4879   0.07717   0.07190  -0.0542   0.0515   1.0000
  17.000   1.4853   0.08083   0.07559  -0.0548   0.0470   1.0000
  17.250   1.4833   0.08448   0.07930  -0.0554   0.0435   1.0000
  17.500   1.4808   0.08823   0.08309  -0.0562   0.0397   1.0000
  17.750   1.4779   0.09212   0.08705  -0.0570   0.0369   1.0000
  18.000   1.4759   0.09594   0.09092  -0.0580   0.0337   1.0000
  18.250   1.4706   0.10030   0.09532  -0.0592   0.0314   1.0000
  18.500   1.4706   0.10389   0.09900  -0.0603   0.0289   1.0000
  18.750   1.4653   0.10835   0.10350  -0.0617   0.0269   1.0000
  19.000   1.4628   0.11241   0.10765  -0.0631   0.0251   1.0000
  19.250   1.4606   0.11645   0.11176  -0.0646   0.0233   1.0000
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