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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 50,000
Max Cl/Cd: 40.21 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe176-il-50000-n5.txt
Download as CSV file: xf-goe176-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 176 (ALBATROS 7020) AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2718   0.10560   0.09933  -0.0305   1.0000   0.1103
  -7.750  -0.2784   0.10008   0.09387  -0.0320   1.0000   0.0679
  -7.500  -0.3006   0.09742   0.09142  -0.0335   1.0000   0.0582
  -7.250  -0.2996   0.09477   0.08887  -0.0320   1.0000   0.0574
  -7.000  -0.3020   0.09236   0.08657  -0.0309   1.0000   0.0567
  -6.750  -0.3065   0.09010   0.08443  -0.0299   1.0000   0.0559
  -6.500  -0.3121   0.08789   0.08234  -0.0291   1.0000   0.0552
  -6.250  -0.3176   0.08561   0.08016  -0.0286   1.0000   0.0543
  -6.000  -0.3157   0.08252   0.07713  -0.0303   0.9983   0.0532
  -5.750  -0.2847   0.07624   0.07080  -0.0402   0.9886   0.0511
  -5.500  -0.2495   0.06879   0.06326  -0.0521   0.9784   0.0490
  -5.250  -0.1975   0.05493   0.04899  -0.0733   0.9686   0.0459
  -5.000  -0.1543   0.04731   0.04092  -0.0844   0.9598   0.0465
  -4.750  -0.1145   0.04320   0.03650  -0.0908   0.9515   0.0497
  -4.500  -0.0657   0.03716   0.02965  -0.0996   0.9443   0.0522
  -4.250  -0.0205   0.03295   0.02459  -0.1052   0.9371   0.0544
  -4.000   0.0232   0.03018   0.02115  -0.1091   0.9296   0.0600
  -3.750   0.0626   0.02843   0.01915  -0.1118   0.9204   0.0666
  -3.500   0.1070   0.02676   0.01721  -0.1151   0.9128   0.0773
  -3.250   0.1472   0.02545   0.01574  -0.1174   0.9021   0.0944
  -3.000   0.1913   0.02440   0.01490  -0.1203   0.8928   0.1445
  -2.750   0.2322   0.02464   0.01502  -0.1221   0.8816   0.2213
  -2.500   0.2659   0.02518   0.01548  -0.1228   0.8680   0.2729
  -2.250   0.2992   0.02507   0.01519  -0.1235   0.8549   0.3032
  -2.000   0.3334   0.02462   0.01446  -0.1243   0.8424   0.3174
  -1.750   0.3677   0.02420   0.01377  -0.1250   0.8299   0.3301
  -1.500   0.4018   0.02382   0.01312  -0.1257   0.8174   0.3428
  -1.250   0.4347   0.02350   0.01257  -0.1261   0.8045   0.3560
  -1.000   0.4648   0.02325   0.01213  -0.1260   0.7899   0.3685
  -0.750   0.4940   0.02300   0.01175  -0.1257   0.7748   0.3809
  -0.500   0.5224   0.02279   0.01143  -0.1253   0.7599   0.3933
  -0.250   0.5502   0.02264   0.01118  -0.1249   0.7457   0.4070
   0.000   0.5777   0.02252   0.01101  -0.1245   0.7319   0.4230
   0.250   0.6051   0.02239   0.01085  -0.1241   0.7182   0.4410
   0.500   0.6323   0.02225   0.01072  -0.1236   0.7041   0.4640
   0.750   0.6590   0.02204   0.01060  -0.1231   0.6899   0.4970
   1.000   0.6843   0.02164   0.01050  -0.1222   0.6755   0.5602
   1.250   0.7051   0.02093   0.01033  -0.1200   0.6609   1.0000
   1.500   0.7325   0.02115   0.01030  -0.1195   0.6457   1.0000
   1.750   0.7594   0.02139   0.01033  -0.1190   0.6303   1.0000
   2.000   0.7860   0.02165   0.01042  -0.1185   0.6149   1.0000
   2.250   0.8123   0.02193   0.01054  -0.1179   0.5990   1.0000
   2.500   0.8383   0.02224   0.01072  -0.1173   0.5830   1.0000
   2.750   0.8642   0.02258   0.01092  -0.1167   0.5670   1.0000
   3.000   0.8899   0.02295   0.01118  -0.1161   0.5515   1.0000
   3.250   0.9155   0.02337   0.01152  -0.1156   0.5367   1.0000
   3.500   0.9411   0.02382   0.01190  -0.1151   0.5231   1.0000
   3.750   0.9671   0.02431   0.01231  -0.1147   0.5112   1.0000
   4.000   0.9930   0.02481   0.01279  -0.1143   0.5003   1.0000
   4.250   1.0175   0.02541   0.01341  -0.1139   0.4894   1.0000
   4.500   1.0430   0.02597   0.01396  -0.1135   0.4803   1.0000
   4.750   1.0679   0.02656   0.01458  -0.1130   0.4714   1.0000
   5.000   1.0923   0.02721   0.01532  -0.1126   0.4633   1.0000
   5.250   1.1174   0.02783   0.01598  -0.1122   0.4563   1.0000
   5.500   1.1419   0.02854   0.01679  -0.1118   0.4501   1.0000
   5.750   1.1657   0.02928   0.01769  -0.1113   0.4437   1.0000
   6.000   1.1900   0.02987   0.01833  -0.1108   0.4368   1.0000
   6.250   1.2114   0.03046   0.01902  -0.1098   0.4271   1.0000
   6.500   1.2317   0.03101   0.01967  -0.1086   0.4162   1.0000
   6.750   1.2522   0.03144   0.02017  -0.1074   0.4047   1.0000
   7.000   1.2726   0.03181   0.02055  -0.1060   0.3926   1.0000
   7.250   1.2925   0.03225   0.02100  -0.1047   0.3807   1.0000
   7.500   1.3099   0.03296   0.02185  -0.1032   0.3694   1.0000
   7.750   1.3297   0.03369   0.02273  -0.1021   0.3606   1.0000
   8.000   1.3503   0.03445   0.02364  -0.1011   0.3532   1.0000
   8.250   1.3704   0.03532   0.02469  -0.1001   0.3467   1.0000
   8.500   1.3889   0.03627   0.02587  -0.0989   0.3398   1.0000
   8.750   1.4109   0.03708   0.02681  -0.0981   0.3337   1.0000
   9.000   1.4251   0.03829   0.02836  -0.0966   0.3268   1.0000
   9.250   1.4468   0.03914   0.02943  -0.0957   0.3208   1.0000
   9.500   1.4571   0.04046   0.03109  -0.0937   0.3128   1.0000
   9.750   1.4682   0.04130   0.03206  -0.0915   0.3013   1.0000
  10.000   1.4697   0.04227   0.03317  -0.0882   0.2871   1.0000
  10.250   1.4638   0.04355   0.03464  -0.0843   0.2740   1.0000
  10.500   1.4534   0.04550   0.03688  -0.0807   0.2621   1.0000
  10.750   1.4452   0.04770   0.03935  -0.0780   0.2508   1.0000
  11.000   1.4378   0.05022   0.04212  -0.0759   0.2399   1.0000
  11.250   1.4293   0.05319   0.04535  -0.0746   0.2284   1.0000
  11.500   1.4184   0.05688   0.04931  -0.0739   0.2170   1.0000
  11.750   1.4053   0.06123   0.05392  -0.0738   0.2059   1.0000
  12.000   1.3934   0.06561   0.05847  -0.0740   0.1945   1.0000
  12.250   1.3842   0.06970   0.06263  -0.0743   0.1825   1.0000
  12.500   1.3759   0.07374   0.06670  -0.0746   0.1712   1.0000
  12.750   1.3661   0.07810   0.07105  -0.0751   0.1600   1.0000
  13.250   1.3381   0.08885   0.08190  -0.0773   0.1406   1.0000
  13.500   1.3238   0.09447   0.08756  -0.0788   0.1307   1.0000
  13.750   1.3100   0.10021   0.09334  -0.0804   0.1206   1.0000
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