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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 500,000
Max Cl/Cd: 86.27 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe711-il-500000.txt
Download as CSV file: xf-goe711-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0501   0.08665   0.08433  -0.1036   0.9717   0.0264
  -8.500  -0.0514   0.08152   0.07922  -0.1093   0.9639   0.0265
  -8.250  -0.0460   0.07657   0.07428  -0.1126   0.9595   0.0268
  -8.000  -0.0303   0.07408   0.07178  -0.1129   0.9569   0.0271
  -7.750  -0.0283   0.07189   0.06960  -0.1124   0.9483   0.0273
  -7.500  -0.0179   0.06877   0.06646  -0.1148   0.9430   0.0277
  -7.250  -0.0121   0.06563   0.06330  -0.1168   0.9344   0.0282
  -7.000  -0.0019   0.06189   0.05951  -0.1200   0.9280   0.0290
  -6.750   0.0106   0.05338   0.05067  -0.1302   0.9178   0.0315
  -6.500   0.0192   0.04775   0.04486  -0.1318   0.9122   0.0319
  -6.250   0.0328   0.04578   0.04290  -0.1313   0.9038   0.0322
  -6.000   0.0505   0.04392   0.04099  -0.1314   0.8978   0.0327
  -5.750   0.0685   0.04191   0.03891  -0.1316   0.8891   0.0334
  -5.500   0.0896   0.03931   0.03615  -0.1324   0.8822   0.0346
  -5.250   0.1120   0.03352   0.02966  -0.1333   0.8724   0.0381
  -5.000   0.1337   0.03138   0.02750  -0.1336   0.8639   0.0386
  -4.750   0.1568   0.02997   0.02604  -0.1338   0.8536   0.0393
  -4.500   0.1808   0.02857   0.02452  -0.1339   0.8421   0.0405
  -4.000   0.2335   0.02426   0.01937  -0.1337   0.8189   0.0460
  -3.750   0.2588   0.02285   0.01789  -0.1339   0.8054   0.0469
  -3.000   0.3395   0.01975   0.01400  -0.1338   0.7606   0.0556
  -2.750   0.3658   0.01866   0.01284  -0.1339   0.7450   0.0571
  -2.500   0.3926   0.01796   0.01199  -0.1339   0.7287   0.0593
  -2.250   0.4204   0.01789   0.01170  -0.1336   0.7120   0.0635
  -2.000   0.4467   0.01657   0.01017  -0.1337   0.6960   0.0685
  -1.750   0.4735   0.01604   0.00954  -0.1337   0.6798   0.0719
  -1.500   0.5002   0.01558   0.00890  -0.1336   0.6631   0.0820
  -1.250   0.5312   0.01387   0.00660  -0.1320   0.6476   0.0449
  -1.000   0.5576   0.01344   0.00606  -0.1317   0.6302   0.0450
  -0.750   0.5836   0.01286   0.00538  -0.1314   0.6133   0.0455
  -0.500   0.6093   0.01244   0.00491  -0.1312   0.5967   0.0468
  -0.250   0.6353   0.01226   0.00466  -0.1309   0.5799   0.0476
   0.000   0.6612   0.01216   0.00448  -0.1306   0.5629   0.0486
   0.250   0.6870   0.01212   0.00434  -0.1303   0.5461   0.0499
   0.500   0.7128   0.01211   0.00425  -0.1301   0.5300   0.0514
   0.750   0.7386   0.01213   0.00419  -0.1298   0.5148   0.0530
   1.000   0.7643   0.01213   0.00410  -0.1295   0.5003   0.0560
   1.250   0.7899   0.01217   0.00407  -0.1292   0.4860   0.0602
   1.500   0.8152   0.01228   0.00408  -0.1289   0.4721   0.0650
   1.750   0.8406   0.01178   0.00418  -0.1290   0.4589   0.3392
   2.000   0.8589   0.01044   0.00440  -0.1270   0.4477   1.0000
   2.250   0.8838   0.01067   0.00450  -0.1266   0.4366   1.0000
   2.750   0.9336   0.01112   0.00475  -0.1259   0.4163   1.0000
   3.000   0.9578   0.01137   0.00491  -0.1254   0.4074   1.0000
   3.250   0.9826   0.01159   0.00506  -0.1250   0.3987   1.0000
   3.500   1.0067   0.01184   0.00523  -0.1245   0.3910   1.0000
   3.750   1.0311   0.01206   0.00540  -0.1241   0.3835   1.0000
   4.000   1.0543   0.01235   0.00561  -0.1234   0.3771   1.0000
   4.250   1.0790   0.01254   0.00579  -0.1231   0.3710   1.0000
   4.500   1.1017   0.01283   0.00600  -0.1224   0.3645   1.0000
   4.750   1.1253   0.01307   0.00621  -0.1218   0.3586   1.0000
   5.000   1.1483   0.01331   0.00643  -0.1211   0.3524   1.0000
   5.250   1.1684   0.01365   0.00669  -0.1199   0.3462   1.0000
   5.500   1.1909   0.01384   0.00690  -0.1191   0.3407   1.0000
   5.750   1.2113   0.01414   0.00717  -0.1180   0.3353   1.0000
   6.000   1.2311   0.01450   0.00749  -0.1168   0.3304   1.0000
   6.250   1.2537   0.01473   0.00775  -0.1161   0.3262   1.0000
   6.500   1.2750   0.01503   0.00804  -0.1152   0.3219   1.0000
   6.750   1.2950   0.01539   0.00839  -0.1141   0.3180   1.0000
   7.000   1.3156   0.01575   0.00874  -0.1131   0.3142   1.0000
   7.250   1.3378   0.01601   0.00905  -0.1125   0.3103   1.0000
   7.500   1.3584   0.01635   0.00939  -0.1116   0.3057   1.0000
   7.750   1.3764   0.01683   0.00982  -0.1102   0.3006   1.0000
   8.000   1.3985   0.01709   0.01014  -0.1096   0.2955   1.0000
   8.250   1.4183   0.01747   0.01052  -0.1087   0.2899   1.0000
   8.500   1.4356   0.01799   0.01101  -0.1073   0.2851   1.0000
   8.750   1.4574   0.01828   0.01137  -0.1067   0.2808   1.0000
   9.000   1.4768   0.01870   0.01181  -0.1058   0.2752   1.0000
   9.250   1.4938   0.01925   0.01234  -0.1045   0.2692   1.0000
   9.500   1.5138   0.01964   0.01278  -0.1037   0.2627   1.0000
   9.750   1.5296   0.02026   0.01337  -0.1023   0.2560   1.0000
  10.000   1.5485   0.02073   0.01388  -0.1014   0.2483   1.0000
  10.250   1.5633   0.02144   0.01456  -0.1000   0.2400   1.0000
  10.500   1.5795   0.02208   0.01521  -0.0988   0.2306   1.0000
  10.750   1.5932   0.02290   0.01600  -0.0973   0.2190   1.0000
  11.000   1.6024   0.02400   0.01702  -0.0952   0.2022   1.0000
  11.250   1.6059   0.02551   0.01839  -0.0925   0.1774   1.0000
  11.500   1.5970   0.02796   0.02060  -0.0885   0.1408   1.0000
  11.750   1.5850   0.03077   0.02323  -0.0845   0.1128   1.0000
  12.000   1.5691   0.03408   0.02637  -0.0806   0.0704   1.0000
  12.250   1.5567   0.03736   0.02961  -0.0774   0.0529   1.0000
  12.500   1.5577   0.03964   0.03197  -0.0757   0.0458   1.0000
  12.750   1.5591   0.04199   0.03439  -0.0743   0.0374   1.0000
  13.250   1.5529   0.04792   0.04034  -0.0716   0.0206   1.0000
  13.500   1.5507   0.05095   0.04347  -0.0706   0.0192   1.0000
  13.750   1.5479   0.05417   0.04680  -0.0698   0.0182   1.0000
  14.000   1.5455   0.05746   0.05022  -0.0692   0.0176   1.0000
  14.250   1.5410   0.06109   0.05397  -0.0688   0.0171   1.0000
  14.500   1.5340   0.06512   0.05813  -0.0685   0.0167   1.0000
  14.750   1.5253   0.06948   0.06262  -0.0684   0.0163   1.0000
  15.000   1.5142   0.07429   0.06757  -0.0685   0.0160   1.0000
  15.250   1.5009   0.07951   0.07293  -0.0688   0.0158   1.0000
  15.500   1.4856   0.08510   0.07865  -0.0692   0.0155   1.0000
  15.750   1.4688   0.09104   0.08475  -0.0700   0.0154   1.0000
  16.000   1.4510   0.09724   0.09109  -0.0709   0.0152   1.0000
  16.250   1.4333   0.10351   0.09750  -0.0720   0.0151   1.0000
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