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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 200,000
Max Cl/Cd: 62.88 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe711-il-200000-n5.txt
Download as CSV file: xf-goe711-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0701   0.09406   0.09050  -0.0942   0.9551   0.0329
  -8.500  -0.0655   0.08942   0.08587  -0.0999   0.9494   0.0331
  -8.250  -0.0626   0.08533   0.08179  -0.1034   0.9427   0.0332
  -7.750  -0.0522   0.07635   0.07279  -0.1120   0.9283   0.0333
  -7.250  -0.0304   0.07054   0.06697  -0.1120   0.9170   0.0344
  -7.000  -0.0217   0.06858   0.06502  -0.1115   0.9082   0.0357
  -6.750  -0.0069   0.06473   0.06109  -0.1157   0.9017   0.0382
  -6.500   0.0043   0.05803   0.05404  -0.1238   0.8901   0.0403
  -6.250   0.0208   0.05376   0.04959  -0.1258   0.8834   0.0403
  -6.000   0.0307   0.05185   0.04785  -0.1236   0.8750   0.0365
  -5.750   0.0496   0.04781   0.04361  -0.1258   0.8666   0.0368
  -5.500   0.0717   0.04389   0.03944  -0.1277   0.8583   0.0373
  -5.250   0.0921   0.03883   0.03398  -0.1290   0.8482   0.0352
  -5.000   0.1179   0.03534   0.03015  -0.1302   0.8395   0.0352
  -4.750   0.1438   0.03326   0.02783  -0.1308   0.8287   0.0366
  -4.500   0.1699   0.03064   0.02487  -0.1313   0.8174   0.0370
  -4.250   0.1977   0.02810   0.02194  -0.1318   0.8067   0.0369
  -3.750   0.2547   0.02438   0.01745  -0.1324   0.7825   0.0383
  -3.500   0.2831   0.02293   0.01564  -0.1326   0.7693   0.0389
  -3.250   0.3116   0.02165   0.01402  -0.1327   0.7557   0.0391
  -3.000   0.3399   0.02060   0.01266  -0.1327   0.7415   0.0394
  -2.750   0.3681   0.01974   0.01150  -0.1327   0.7270   0.0397
  -2.500   0.3959   0.01913   0.01060  -0.1325   0.7117   0.0403
  -2.250   0.4229   0.01834   0.00965  -0.1325   0.6963   0.0414
  -2.000   0.4497   0.01783   0.00901  -0.1323   0.6808   0.0423
  -1.750   0.4764   0.01737   0.00839  -0.1321   0.6653   0.0427
  -1.500   0.5027   0.01698   0.00787  -0.1318   0.6492   0.0433
  -1.250   0.5287   0.01666   0.00742  -0.1315   0.6329   0.0439
  -1.000   0.5545   0.01639   0.00704  -0.1311   0.6169   0.0447
  -0.750   0.5801   0.01617   0.00672  -0.1307   0.6013   0.0456
  -0.500   0.6055   0.01603   0.00647  -0.1303   0.5859   0.0470
   0.000   0.6556   0.01583   0.00609  -0.1294   0.5546   0.0501
   0.250   0.6805   0.01572   0.00591  -0.1290   0.5396   0.0516
   0.500   0.7055   0.01571   0.00581  -0.1287   0.5256   0.0534
   0.750   0.7305   0.01574   0.00575  -0.1283   0.5122   0.0558
   1.000   0.7551   0.01582   0.00571  -0.1278   0.4990   0.0587
   1.250   0.7795   0.01590   0.00570  -0.1273   0.4863   0.0649
   1.500   0.8038   0.01599   0.00573  -0.1268   0.4739   0.0770
   1.750   0.8219   0.01400   0.00601  -0.1249   0.4634   1.0000
   2.000   0.8457   0.01426   0.00608  -0.1243   0.4533   1.0000
   2.250   0.8695   0.01452   0.00620  -0.1236   0.4430   1.0000
   2.500   0.8932   0.01478   0.00633  -0.1231   0.4333   1.0000
   3.000   0.9398   0.01534   0.00667  -0.1218   0.4154   1.0000
   3.250   0.9621   0.01565   0.00686  -0.1210   0.4077   1.0000
   3.500   0.9859   0.01591   0.00706  -0.1204   0.4004   1.0000
   3.750   1.0082   0.01622   0.00729  -0.1196   0.3937   1.0000
   4.000   1.0312   0.01651   0.00752  -0.1190   0.3873   1.0000
   4.250   1.0534   0.01682   0.00777  -0.1182   0.3807   1.0000
   4.500   1.0748   0.01716   0.00805  -0.1173   0.3751   1.0000
   4.750   1.0973   0.01745   0.00832  -0.1166   0.3692   1.0000
   5.000   1.1180   0.01778   0.00861  -0.1155   0.3639   1.0000
   5.250   1.1378   0.01816   0.00893  -0.1143   0.3596   1.0000
   5.500   1.1596   0.01846   0.00925  -0.1135   0.3550   1.0000
   5.750   1.1803   0.01881   0.00960  -0.1125   0.3505   1.0000
   6.000   1.1998   0.01923   0.00997  -0.1114   0.3459   1.0000
   6.250   1.2200   0.01961   0.01035  -0.1104   0.3411   1.0000
   6.500   1.2400   0.01999   0.01075  -0.1093   0.3357   1.0000
   6.750   1.2588   0.02043   0.01117  -0.1081   0.3309   1.0000
   7.000   1.2781   0.02088   0.01162  -0.1070   0.3266   1.0000
   7.250   1.2985   0.02128   0.01206  -0.1062   0.3224   1.0000
   7.500   1.3179   0.02172   0.01253  -0.1051   0.3183   1.0000
   7.750   1.3361   0.02223   0.01304  -0.1040   0.3144   1.0000
   8.000   1.3549   0.02272   0.01356  -0.1029   0.3106   1.0000
   8.250   1.3742   0.02318   0.01408  -0.1020   0.3064   1.0000
   8.500   1.3922   0.02369   0.01464  -0.1008   0.3024   1.0000
   8.750   1.4090   0.02428   0.01524  -0.0996   0.2987   1.0000
   9.000   1.4265   0.02485   0.01586  -0.0984   0.2949   1.0000
   9.250   1.4436   0.02540   0.01650  -0.0973   0.2897   1.0000
   9.500   1.4571   0.02611   0.01722  -0.0957   0.2836   1.0000
   9.750   1.4713   0.02681   0.01799  -0.0942   0.2770   1.0000
  10.000   1.4844   0.02758   0.01880  -0.0926   0.2697   1.0000
  10.250   1.4970   0.02842   0.01968  -0.0911   0.2637   1.0000
  10.500   1.5110   0.02921   0.02055  -0.0898   0.2568   1.0000
  10.750   1.5207   0.03027   0.02163  -0.0880   0.2504   1.0000
  11.000   1.5334   0.03119   0.02264  -0.0867   0.2414   1.0000
  11.250   1.5419   0.03240   0.02387  -0.0850   0.2320   1.0000
  11.500   1.5491   0.03377   0.02525  -0.0832   0.2215   1.0000
  11.750   1.5560   0.03522   0.02672  -0.0816   0.2091   1.0000
  12.000   1.5593   0.03699   0.02850  -0.0798   0.1948   1.0000
  12.250   1.5591   0.03913   0.03061  -0.0778   0.1778   1.0000
  12.500   1.5525   0.04198   0.03337  -0.0756   0.1550   1.0000
  12.750   1.5395   0.04562   0.03690  -0.0733   0.1323   1.0000
  13.000   1.5240   0.04973   0.04094  -0.0713   0.1135   1.0000
  13.250   1.5056   0.05443   0.04559  -0.0696   0.0722   1.0000
  13.500   1.4814   0.06007   0.05118  -0.0683   0.0595   1.0000
  13.750   1.4673   0.06483   0.05603  -0.0677   0.0529   1.0000
  14.000   1.4572   0.06927   0.06062  -0.0674   0.0479   1.0000
  14.250   1.4505   0.07342   0.06491  -0.0674   0.0424   1.0000
  14.750   1.4270   0.08333   0.07503  -0.0679   0.0239   1.0000
  15.000   1.4135   0.08872   0.08050  -0.0685   0.0219   1.0000
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