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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.23 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe711-il-1000000-n5.txt
Download as CSV file: xf-goe711-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1165   0.08981   0.08793  -0.0917   0.9259   0.0104
  -9.750  -0.1104   0.08695   0.08507  -0.0931   0.9201   0.0107
  -9.250  -0.1330   0.07405   0.07215  -0.1002   0.9064   0.0125
  -9.000  -0.1289   0.07109   0.06916  -0.1022   0.8985   0.0126
  -8.000  -0.1933   0.02112   0.01737  -0.1311   0.8562   0.0190
  -7.750  -0.1663   0.02088   0.01705  -0.1312   0.8447   0.0191
  -7.500  -0.1394   0.02067   0.01675  -0.1313   0.8310   0.0192
  -7.250  -0.1131   0.02043   0.01637  -0.1313   0.8127   0.0193
  -7.000  -0.0867   0.02026   0.01607  -0.1312   0.7920   0.0195
  -6.750  -0.0599   0.02020   0.01589  -0.1312   0.7722   0.0196
  -6.500  -0.0335   0.01979   0.01533  -0.1313   0.7562   0.0199
  -6.250  -0.0083   0.01857   0.01387  -0.1313   0.7404   0.0204
  -6.000   0.0158   0.01643   0.01133  -0.1313   0.7254   0.0213
  -5.750   0.0419   0.01525   0.00987  -0.1313   0.7106   0.0220
  -5.500   0.0689   0.01449   0.00887  -0.1314   0.6962   0.0224
  -5.250   0.0962   0.01399   0.00819  -0.1314   0.6806   0.0226
  -5.000   0.1237   0.01360   0.00763  -0.1315   0.6643   0.0228
  -4.750   0.1506   0.01286   0.00672  -0.1316   0.6490   0.0232
  -4.500   0.1784   0.01267   0.00643  -0.1318   0.6342   0.0236
  -4.250   0.2062   0.01254   0.00621  -0.1319   0.6184   0.0239
  -4.000   0.2339   0.01238   0.00594  -0.1320   0.6013   0.0242
  -3.750   0.2615   0.01219   0.00564  -0.1321   0.5848   0.0245
  -3.500   0.2892   0.01200   0.00534  -0.1322   0.5696   0.0247
  -3.250   0.3170   0.01181   0.00506  -0.1323   0.5550   0.0251
  -3.000   0.3446   0.01165   0.00480  -0.1324   0.5397   0.0254
  -2.750   0.3721   0.01151   0.00456  -0.1325   0.5238   0.0257
  -2.500   0.3997   0.01139   0.00434  -0.1325   0.5084   0.0260
  -2.250   0.4274   0.01128   0.00415  -0.1326   0.4953   0.0264
  -2.000   0.4551   0.01120   0.00398  -0.1328   0.4828   0.0267
  -1.750   0.4827   0.01116   0.00386  -0.1329   0.4696   0.0270
  -1.500   0.5101   0.01116   0.00378  -0.1329   0.4557   0.0273
  -1.250   0.5377   0.01112   0.00366  -0.1330   0.4427   0.0277
  -1.000   0.5653   0.01101   0.00349  -0.1332   0.4319   0.0283
  -0.750   0.5929   0.01100   0.00342  -0.1333   0.4218   0.0289
  -0.500   0.6204   0.01101   0.00338  -0.1334   0.4112   0.0294
  -0.250   0.6479   0.01104   0.00336  -0.1335   0.4011   0.0300
   0.000   0.6751   0.01110   0.00336  -0.1336   0.3910   0.0306
   0.250   0.7027   0.01112   0.00335  -0.1337   0.3825   0.0312
   0.500   0.7299   0.01118   0.00336  -0.1337   0.3748   0.0320
   0.750   0.7575   0.01122   0.00337  -0.1339   0.3680   0.0327
   1.250   0.8118   0.01135   0.00343  -0.1340   0.3542   0.0357
   1.500   0.8385   0.01144   0.00349  -0.1340   0.3469   0.0378
   1.750   0.8655   0.01152   0.00356  -0.1340   0.3414   0.0400
   2.000   0.8925   0.01159   0.00362  -0.1340   0.3364   0.0450
   2.250   0.9190   0.01168   0.00371  -0.1340   0.3313   0.0545
   2.500   0.9430   0.01021   0.00409  -0.1344   0.3272   0.8266
   2.750   0.9642   0.00998   0.00417  -0.1328   0.3236   1.0000
   3.000   0.9901   0.01017   0.00428  -0.1326   0.3169   1.0000
   3.250   1.0156   0.01036   0.00441  -0.1324   0.3100   1.0000
   3.500   1.0411   0.01055   0.00454  -0.1322   0.3028   1.0000
   3.750   1.0659   0.01078   0.00469  -0.1319   0.2958   1.0000
   4.000   1.0915   0.01094   0.00483  -0.1317   0.2909   1.0000
   4.250   1.1166   0.01112   0.00498  -0.1314   0.2869   1.0000
   4.500   1.1411   0.01133   0.00514  -0.1311   0.2827   1.0000
   4.750   1.1659   0.01151   0.00530  -0.1308   0.2796   1.0000
   5.000   1.1905   0.01168   0.00547  -0.1304   0.2762   1.0000
   5.250   1.2145   0.01188   0.00565  -0.1300   0.2723   1.0000
   5.500   1.2367   0.01211   0.00585  -0.1292   0.2682   1.0000
   5.750   1.2583   0.01234   0.00607  -0.1282   0.2641   1.0000
   6.000   1.2800   0.01258   0.00629  -0.1273   0.2595   1.0000
   6.250   1.3008   0.01287   0.00655  -0.1263   0.2537   1.0000
   6.500   1.3218   0.01316   0.00682  -0.1253   0.2487   1.0000
   6.750   1.3433   0.01344   0.00709  -0.1245   0.2435   1.0000
   7.000   1.3622   0.01385   0.00744  -0.1232   0.2338   1.0000
   7.250   1.3797   0.01435   0.00785  -0.1217   0.2203   1.0000
   7.500   1.3965   0.01489   0.00831  -0.1201   0.2065   1.0000
   7.750   1.4127   0.01548   0.00881  -0.1185   0.1926   1.0000
   8.000   1.4263   0.01621   0.00943  -0.1164   0.1735   1.0000
   8.250   1.4225   0.01794   0.01084  -0.1116   0.1249   1.0000
   8.500   1.4328   0.01890   0.01172  -0.1092   0.1084   1.0000
   8.750   1.4442   0.01981   0.01256  -0.1070   0.0947   1.0000
   9.000   1.4438   0.02147   0.01406  -0.1031   0.0563   1.0000
   9.250   1.4590   0.02220   0.01480  -0.1017   0.0517   1.0000
   9.500   1.4737   0.02296   0.01560  -0.1003   0.0484   1.0000
   9.750   1.4889   0.02369   0.01636  -0.0989   0.0458   1.0000
  10.000   1.5038   0.02446   0.01715  -0.0977   0.0431   1.0000
  10.250   1.5165   0.02539   0.01809  -0.0961   0.0385   1.0000
  10.750   1.5318   0.02802   0.02067  -0.0920   0.0147   1.0000
  11.000   1.5428   0.02915   0.02184  -0.0905   0.0131   1.0000
  11.250   1.5542   0.03028   0.02301  -0.0892   0.0121   1.0000
  11.500   1.5644   0.03153   0.02430  -0.0878   0.0113   1.0000
  11.750   1.5733   0.03293   0.02575  -0.0863   0.0105   1.0000
  12.000   1.5831   0.03430   0.02718  -0.0851   0.0100   1.0000
  12.250   1.5922   0.03576   0.02869  -0.0839   0.0096   1.0000
  12.500   1.6002   0.03737   0.03036  -0.0827   0.0090   1.0000
  12.750   1.6070   0.03914   0.03218  -0.0816   0.0086   1.0000
  13.000   1.6120   0.04115   0.03425  -0.0804   0.0081   1.0000
  13.250   1.6173   0.04320   0.03636  -0.0794   0.0078   1.0000
  13.500   1.6225   0.04532   0.03855  -0.0786   0.0076   1.0000
  13.750   1.6262   0.04762   0.04093  -0.0777   0.0073   1.0000
  14.000   1.6290   0.05010   0.04348  -0.0770   0.0071   1.0000
  14.250   1.6305   0.05278   0.04623  -0.0763   0.0068   1.0000
  14.500   1.6306   0.05569   0.04923  -0.0757   0.0066   1.0000
  14.750   1.6293   0.05886   0.05248  -0.0753   0.0064   1.0000
  15.000   1.6260   0.06231   0.05601  -0.0749   0.0062   1.0000
  15.250   1.6202   0.06614   0.05994  -0.0746   0.0060   1.0000
  15.500   1.6133   0.07021   0.06411  -0.0745   0.0059   1.0000
  15.750   1.6075   0.07422   0.06822  -0.0745   0.0058   1.0000
  16.000   1.6004   0.07846   0.07257  -0.0746   0.0057   1.0000
  16.250   1.5921   0.08290   0.07711  -0.0749   0.0056   1.0000
  16.500   1.5816   0.08771   0.08203  -0.0753   0.0055   1.0000
  16.750   1.5704   0.09269   0.08712  -0.0758   0.0054   1.0000
  17.000   1.5589   0.09778   0.09231  -0.0765   0.0053   1.0000
  17.250   1.5468   0.10298   0.09762  -0.0773   0.0052   1.0000
  17.500   1.5341   0.10830   0.10305  -0.0782   0.0051   1.0000
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