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EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 200,000
Max Cl/Cd: 61.16 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ste87391-il-200000-n5.txt
Download as CSV file: xf-ste87391-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4381   0.06765   0.06322  -0.1266   0.9517   0.0170
 -12.250  -0.4642   0.06027   0.05559  -0.1324   0.9496   0.0168
 -12.000  -0.4783   0.05479   0.04989  -0.1374   0.9478   0.0168
 -11.750  -0.5131   0.05327   0.04831  -0.1316   0.9429   0.0168
 -11.500  -0.5354   0.05088   0.04578  -0.1292   0.9389   0.0168
 -11.250  -0.5515   0.04852   0.04327  -0.1275   0.9361   0.0168
 -11.000  -0.5607   0.04624   0.04081  -0.1266   0.9339   0.0169
 -10.750  -0.5902   0.04544   0.03994  -0.1192   0.9281   0.0169
 -10.500  -0.5927   0.04344   0.03777  -0.1173   0.9247   0.0171
 -10.250  -0.5858   0.04140   0.03550  -0.1167   0.9227   0.0173
 -10.000  -0.5732   0.03946   0.03334  -0.1167   0.9212   0.0176
  -9.750  -0.5549   0.03760   0.03125  -0.1173   0.9201   0.0180
  -9.500  -0.5629   0.03669   0.03023  -0.1121   0.9153   0.0182
  -9.250  -0.5498   0.03531   0.02866  -0.1109   0.9126   0.0186
  -9.000  -0.5302   0.03401   0.02717  -0.1108   0.9108   0.0192
  -8.750  -0.5080   0.03286   0.02581  -0.1109   0.9094   0.0200
  -8.500  -0.4831   0.03174   0.02449  -0.1114   0.9083   0.0207
  -8.250  -0.4561   0.03067   0.02322  -0.1121   0.9074   0.0210
  -8.000  -0.4289   0.02934   0.02181  -0.1130   0.9066   0.0215
  -7.750  -0.4201   0.02856   0.02099  -0.1103   0.9028   0.0219
  -7.500  -0.4007   0.02774   0.02012  -0.1096   0.9000   0.0225
  -7.250  -0.3755   0.02698   0.01931  -0.1099   0.8981   0.0231
  -7.000  -0.3479   0.02630   0.01855  -0.1106   0.8967   0.0239
  -6.750  -0.3181   0.02570   0.01787  -0.1117   0.8954   0.0253
  -6.500  -0.2868   0.02515   0.01722  -0.1130   0.8943   0.0266
  -6.250  -0.2544   0.02457   0.01655  -0.1145   0.8935   0.0276
  -6.000  -0.2212   0.02399   0.01587  -0.1162   0.8927   0.0292
  -5.750  -0.2069   0.02378   0.01561  -0.1142   0.8879   0.0306
  -5.500  -0.1805   0.02348   0.01522  -0.1144   0.8853   0.0329
  -5.250  -0.1500   0.02311   0.01480  -0.1153   0.8834   0.0371
  -5.000  -0.1172   0.02256   0.01434  -0.1168   0.8820   0.0575
  -4.750  -0.0825   0.02176   0.01404  -0.1193   0.8810   0.1503
  -4.500  -0.0490   0.02158   0.01391  -0.1207   0.8799   0.1833
  -4.250  -0.0149   0.02143   0.01381  -0.1223   0.8790   0.2109
  -4.000   0.0018   0.02151   0.01388  -0.1206   0.8737   0.2248
  -3.750   0.0289   0.02144   0.01384  -0.1208   0.8705   0.2420
  -3.500   0.0604   0.02130   0.01373  -0.1219   0.8685   0.2597
  -3.250   0.0937   0.02113   0.01360  -0.1232   0.8669   0.2778
  -3.000   0.1283   0.02094   0.01344  -0.1248   0.8657   0.2943
  -2.750   0.1636   0.02074   0.01327  -0.1265   0.8647   0.3110
  -2.500   0.1778   0.02086   0.01343  -0.1243   0.8573   0.3253
  -2.250   0.2099   0.02068   0.01331  -0.1254   0.8547   0.3490
  -2.000   0.2448   0.02041   0.01316  -0.1271   0.8530   0.3830
  -1.750   0.2812   0.02008   0.01299  -0.1291   0.8516   0.4299
  -1.500   0.3050   0.01998   0.01309  -0.1287   0.8462   0.4815
  -1.250   0.3334   0.01974   0.01314  -0.1291   0.8418   0.5529
  -1.000   0.3624   0.01947   0.01324  -0.1288   0.8392   0.6393
  -0.750   0.3920   0.01930   0.01320  -0.1285   0.8372   0.6983
  -0.500   0.4074   0.01954   0.01343  -0.1262   0.8282   0.7239
  -0.250   0.4395   0.01932   0.01319  -0.1267   0.8251   0.7424
   0.000   0.4709   0.01909   0.01293  -0.1272   0.8217   0.7559
   0.250   0.4909   0.01916   0.01299  -0.1257   0.8126   0.7676
   0.500   0.5232   0.01873   0.01255  -0.1260   0.8095   0.7770
   0.750   0.5407   0.01881   0.01264  -0.1240   0.7985   0.7854
   1.000   0.5631   0.01871   0.01255  -0.1228   0.7897   0.7933
   1.250   0.5902   0.01841   0.01224  -0.1223   0.7830   0.8005
   1.500   0.6111   0.01842   0.01226  -0.1209   0.7725   0.8074
   1.750   0.6424   0.01798   0.01182  -0.1211   0.7671   0.8149
   2.000   0.6638   0.01794   0.01181  -0.1196   0.7557   0.8253
   2.250   0.6860   0.01771   0.01161  -0.1178   0.7455   0.8398
   2.500   0.7130   0.01719   0.01111  -0.1167   0.7366   0.8535
   2.750   0.7448   0.01668   0.01059  -0.1169   0.7242   0.8602
   3.000   0.7820   0.01606   0.00992  -0.1183   0.7092   0.8633
   3.250   0.8218   0.01549   0.00928  -0.1202   0.6897   0.8656
   3.500   0.8618   0.01505   0.00871  -0.1222   0.6648   0.8677
   3.750   0.8959   0.01493   0.00841  -0.1233   0.6342   0.8697
   4.000   0.9228   0.01510   0.00841  -0.1233   0.6011   0.8718
   4.250   0.9424   0.01541   0.00856  -0.1218   0.5694   0.8738
   4.500   0.9599   0.01582   0.00882  -0.1201   0.5392   0.8759
   4.750   0.9759   0.01630   0.00916  -0.1182   0.5094   0.8784
   5.250   1.0078   0.01740   0.01001  -0.1146   0.4530   0.8827
   5.500   1.0245   0.01797   0.01048  -0.1131   0.4284   0.8850
   5.750   1.0409   0.01851   0.01094  -0.1114   0.4066   0.8873
   6.000   1.0569   0.01905   0.01140  -0.1097   0.3873   0.8893
   6.250   1.0739   0.01958   0.01190  -0.1082   0.3688   0.8913
   6.500   1.0910   0.02014   0.01241  -0.1068   0.3514   0.8935
   6.750   1.1088   0.02070   0.01293  -0.1056   0.3358   0.8957
   7.000   1.1268   0.02126   0.01347  -0.1044   0.3221   0.8981
   7.250   1.1447   0.02184   0.01404  -0.1032   0.3105   0.9008
   7.500   1.1621   0.02235   0.01457  -0.1018   0.2998   0.9033
   7.750   1.1802   0.02288   0.01512  -0.1006   0.2901   0.9058
   8.000   1.1974   0.02348   0.01572  -0.0993   0.2811   0.9085
   8.250   1.2161   0.02402   0.01631  -0.0983   0.2723   0.9113
   8.500   1.2338   0.02463   0.01696  -0.0972   0.2651   0.9143
   8.750   1.2512   0.02516   0.01756  -0.0959   0.2576   0.9176
   9.000   1.2672   0.02579   0.01822  -0.0944   0.2505   0.9215
   9.250   1.2841   0.02637   0.01887  -0.0932   0.2421   0.9263
   9.500   1.2981   0.02703   0.01957  -0.0915   0.2321   0.9326
   9.750   1.3098   0.02777   0.02033  -0.0895   0.2206   0.9418
  10.000   1.3191   0.02842   0.02100  -0.0872   0.2081   0.9671
  10.250   1.3323   0.02927   0.02186  -0.0858   0.1936   0.9981
  10.500   1.3475   0.03018   0.02279  -0.0847   0.1802   0.9981
  10.750   1.3613   0.03119   0.02379  -0.0836   0.1654   0.9981
  11.000   1.3738   0.03231   0.02488  -0.0823   0.1462   0.9981
  11.250   1.3827   0.03370   0.02616  -0.0806   0.1213   0.9981
  11.500   1.3864   0.03551   0.02780  -0.0785   0.0910   0.9981
  11.750   1.3877   0.03757   0.02969  -0.0762   0.0660   0.9981
  12.000   1.3885   0.03974   0.03175  -0.0740   0.0463   0.9981
  12.250   1.3891   0.04197   0.03393  -0.0719   0.0323   0.9981
  12.500   1.3903   0.04419   0.03616  -0.0699   0.0233   0.9981
  12.750   1.3916   0.04647   0.03849  -0.0682   0.0183   0.9981
  13.000   1.3932   0.04879   0.04090  -0.0666   0.0156   0.9981
  13.250   1.3944   0.05122   0.04344  -0.0651   0.0140   0.9981
  13.500   1.3954   0.05374   0.04609  -0.0638   0.0129   0.9981
  13.750   1.3946   0.05652   0.04899  -0.0627   0.0121   0.9981
  14.000   1.3913   0.05968   0.05229  -0.0616   0.0114   0.9981
  14.250   1.3903   0.06269   0.05545  -0.0609   0.0110   0.9981
  14.500   1.3876   0.06599   0.05891  -0.0604   0.0105   0.9981
  14.750   1.3838   0.06953   0.06259  -0.0600   0.0100   0.9981
  15.000   1.3786   0.07334   0.06655  -0.0600   0.0097   0.9981
  15.250   1.3722   0.07746   0.07082  -0.0601   0.0094   0.9981
  15.500   1.3634   0.08205   0.07555  -0.0606   0.0091   0.9981
  15.750   1.3539   0.08687   0.08052  -0.0614   0.0089   0.9981
  16.000   1.3432   0.09200   0.08580  -0.0625   0.0088   0.9981
  16.250   1.3312   0.09747   0.09143  -0.0640   0.0087   0.9981
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