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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 100,000
Max Cl/Cd: 44.59 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ec863914-il-100000-n5.txt
Download as CSV file: xf-ec863914-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5061   0.09674   0.09195  -0.0541   0.9951   0.0154
 -10.500  -0.5200   0.08943   0.08455  -0.0589   0.9931   0.0153
 -10.250  -0.5338   0.08255   0.07758  -0.0642   0.9906   0.0152
 -10.000  -0.5503   0.07596   0.07087  -0.0694   0.9881   0.0151
  -9.750  -0.5661   0.07042   0.06519  -0.0738   0.9850   0.0150
  -9.500  -0.5830   0.06637   0.06100  -0.0754   0.9810   0.0149
  -9.250  -0.5990   0.06284   0.05731  -0.0767   0.9766   0.0149
  -9.000  -0.6108   0.05959   0.05387  -0.0780   0.9724   0.0148
  -8.750  -0.6164   0.05609   0.05012  -0.0793   0.9675   0.0147
  -8.500  -0.6098   0.05232   0.04601  -0.0822   0.9638   0.0146
  -8.250  -0.5942   0.04888   0.04221  -0.0850   0.9612   0.0145
  -8.000  -0.5844   0.04616   0.03920  -0.0850   0.9572   0.0144
  -7.750  -0.5652   0.04367   0.03641  -0.0861   0.9541   0.0143
  -7.500  -0.5413   0.04146   0.03393  -0.0875   0.9518   0.0142
  -7.250  -0.5146   0.03957   0.03179  -0.0888   0.9500   0.0141
  -7.000  -0.4926   0.03797   0.03002  -0.0890   0.9471   0.0141
  -6.750  -0.4704   0.03651   0.02839  -0.0891   0.9438   0.0141
  -6.500  -0.4435   0.03522   0.02696  -0.0901   0.9412   0.0141
  -6.250  -0.4125   0.03401   0.02560  -0.0921   0.9390   0.0142
  -6.000  -0.3779   0.03290   0.02431  -0.0948   0.9372   0.0142
  -5.750  -0.3430   0.03188   0.02307  -0.0975   0.9353   0.0144
  -5.500  -0.3162   0.03103   0.02205  -0.0985   0.9315   0.0145
  -5.250  -0.2830   0.03029   0.02105  -0.1006   0.9287   0.0147
  -5.000  -0.2478   0.02968   0.02022  -0.1028   0.9264   0.0150
  -4.750  -0.2113   0.02923   0.01960  -0.1051   0.9244   0.0154
  -4.500  -0.1733   0.02882   0.01903  -0.1076   0.9228   0.0163
  -4.250  -0.1485   0.02845   0.01857  -0.1076   0.9181   0.0173
  -4.000  -0.1153   0.02808   0.01816  -0.1091   0.9149   0.0227
  -3.750  -0.0751   0.02692   0.01793  -0.1132   0.9134   0.1849
  -3.500  -0.0391   0.02695   0.01782  -0.1150   0.9112   0.1996
  -3.250  -0.0115   0.02685   0.01779  -0.1155   0.9066   0.2311
  -3.000   0.0208   0.02676   0.01775  -0.1168   0.9028   0.2549
  -2.750   0.0570   0.02671   0.01772  -0.1188   0.9002   0.2756
  -2.500   0.0916   0.02654   0.01774  -0.1208   0.8968   0.3161
  -2.250   0.1219   0.02642   0.01771  -0.1219   0.8918   0.3472
  -2.000   0.1617   0.02611   0.01782  -0.1249   0.8893   0.4303
  -1.750   0.1761   0.02625   0.01873  -0.1213   0.8833   0.5437
  -1.500   0.1990   0.02660   0.01916  -0.1195   0.8780   0.5991
  -1.250   0.2311   0.02682   0.01926  -0.1203   0.8734   0.6318
  -1.000   0.2619   0.02701   0.01934  -0.1210   0.8674   0.6553
  -0.750   0.2963   0.02714   0.01939  -0.1218   0.8642   0.6714
  -0.500   0.3181   0.02734   0.01952  -0.1208   0.8558   0.6846
  -0.250   0.3512   0.02736   0.01949  -0.1212   0.8523   0.6962
   0.000   0.3692   0.02749   0.01962  -0.1191   0.8430   0.7048
   0.250   0.4057   0.02735   0.01942  -0.1203   0.8394   0.7153
   0.500   0.4241   0.02738   0.01946  -0.1183   0.8291   0.7232
   0.750   0.4496   0.02729   0.01935  -0.1176   0.8201   0.7312
   1.000   0.4813   0.02695   0.01901  -0.1176   0.8139   0.7393
   1.250   0.5009   0.02690   0.01898  -0.1157   0.8031   0.7481
   1.500   0.5337   0.02645   0.01855  -0.1156   0.7982   0.7603
   1.750   0.5495   0.02640   0.01855  -0.1127   0.7861   0.7710
   2.000   0.5682   0.02619   0.01839  -0.1103   0.7747   0.7799
   2.250   0.5990   0.02573   0.01794  -0.1103   0.7657   0.7894
   2.500   0.6211   0.02525   0.01750  -0.1083   0.7550   0.7958
   3.000   0.6789   0.02459   0.01690  -0.1081   0.7284   0.8061
   3.250   0.7100   0.02411   0.01644  -0.1082   0.7143   0.8087
   3.500   0.7445   0.02360   0.01596  -0.1090   0.6990   0.8111
   3.750   0.7826   0.02304   0.01538  -0.1104   0.6814   0.8135
   4.000   0.8212   0.02258   0.01490  -0.1120   0.6590   0.8158
   4.250   0.8633   0.02211   0.01435  -0.1143   0.6316   0.8176
   4.500   0.9034   0.02185   0.01399  -0.1163   0.5983   0.8194
   4.750   0.9365   0.02175   0.01376  -0.1169   0.5624   0.8211
   5.000   0.9658   0.02191   0.01376  -0.1171   0.5251   0.8229
   5.250   0.9917   0.02227   0.01397  -0.1169   0.4880   0.8245
   5.500   1.0153   0.02277   0.01431  -0.1165   0.4541   0.8262
   5.750   1.0377   0.02334   0.01475  -0.1159   0.4239   0.8281
   6.000   1.0601   0.02394   0.01527  -0.1154   0.3973   0.8303
   6.250   1.0827   0.02459   0.01584  -0.1151   0.3736   0.8323
   6.500   1.1057   0.02528   0.01649  -0.1148   0.3524   0.8341
   6.750   1.1263   0.02592   0.01710  -0.1141   0.3348   0.8355
   7.000   1.1471   0.02657   0.01773  -0.1133   0.3195   0.8370
   7.250   1.1687   0.02720   0.01839  -0.1127   0.3066   0.8388
   7.500   1.1909   0.02784   0.01911  -0.1122   0.2955   0.8408
   7.750   1.2132   0.02855   0.01984  -0.1118   0.2857   0.8430
   8.000   1.2362   0.02925   0.02062  -0.1116   0.2760   0.8450
   8.250   1.2601   0.02997   0.02143  -0.1115   0.2674   0.8468
   8.500   1.2842   0.03074   0.02226  -0.1114   0.2601   0.8486
   8.750   1.3077   0.03144   0.02309  -0.1111   0.2537   0.8502
   9.000   1.3301   0.03216   0.02398  -0.1107   0.2474   0.8519
   9.250   1.3477   0.03296   0.02491  -0.1096   0.2380   0.8540
   9.500   1.3590   0.03387   0.02590  -0.1077   0.2254   0.8563
   9.750   1.3701   0.03487   0.02697  -0.1060   0.2126   0.8589
  10.000   1.3837   0.03588   0.02813  -0.1047   0.2014   0.8614
  10.250   1.3916   0.03707   0.02940  -0.1027   0.1856   0.8636
  10.500   1.3983   0.03832   0.03074  -0.1007   0.1612   0.8658
  11.000   1.3924   0.04344   0.03506  -0.0958   0.0522   0.8697
  11.250   1.3856   0.04689   0.03833  -0.0932   0.0266   0.8715
  11.500   1.3848   0.04982   0.04139  -0.0912   0.0193   0.8735
  11.750   1.3833   0.05288   0.04460  -0.0895   0.0163   0.8755
  12.000   1.3825   0.05573   0.04767  -0.0879   0.0149   0.8776
  12.250   1.3798   0.05885   0.05104  -0.0865   0.0138   0.8799
  12.500   1.3752   0.06236   0.05479  -0.0854   0.0130   0.8824
  12.750   1.3686   0.06634   0.05900  -0.0848   0.0124   0.8849
  13.000   1.3601   0.07081   0.06371  -0.0847   0.0120   0.8873
  13.250   1.3483   0.07593   0.06907  -0.0850   0.0116   0.8895
  13.500   1.3347   0.08153   0.07491  -0.0859   0.0114   0.8917
  13.750   1.3215   0.08750   0.08110  -0.0875   0.0111   0.8938
  14.000   1.3092   0.09374   0.08759  -0.0897   0.0110   0.8959
  14.250   1.2959   0.10048   0.09457  -0.0924   0.0107   0.8980
  14.500   1.2826   0.10761   0.10192  -0.0957   0.0107   0.9000
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