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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 200,000
Max Cl/Cd: 73.59 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe176-il-200000-n5.txt
Download as CSV file: xf-goe176-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2867   0.10773   0.10433  -0.0346   1.0000   0.0238
  -9.000  -0.2846   0.10463   0.10128  -0.0351   1.0000   0.0238
  -8.750  -0.2834   0.10156   0.09826  -0.0353   1.0000   0.0238
  -8.250  -0.1770   0.07409   0.07107  -0.0468   0.9781   0.0161
  -7.750  -0.2742   0.08540   0.08226  -0.0378   0.9936   0.0158
  -7.500  -0.2601   0.08102   0.07791  -0.0424   0.9821   0.0155
  -7.250  -0.2473   0.07644   0.07334  -0.0471   0.9627   0.0152
  -7.000  -0.2300   0.07108   0.06799  -0.0539   0.9430   0.0150
  -6.750  -0.2030   0.06404   0.06091  -0.0646   0.9279   0.0147
  -6.500  -0.1677   0.05450   0.05127  -0.0800   0.9142   0.0145
  -6.250  -0.1063   0.02920   0.02480  -0.1165   0.9011   0.0140
  -6.000  -0.0634   0.02481   0.01964  -0.1230   0.8891   0.0154
  -5.750  -0.0240   0.02194   0.01609  -0.1268   0.8751   0.0161
  -5.500   0.0116   0.01970   0.01334  -0.1291   0.8600   0.0167
  -5.250   0.0435   0.01796   0.01131  -0.1305   0.8453   0.0176
  -5.000   0.0739   0.01701   0.01017  -0.1311   0.8312   0.0188
  -4.750   0.1034   0.01636   0.00932  -0.1315   0.8166   0.0211
  -4.500   0.1323   0.01563   0.00837  -0.1315   0.8017   0.0229
  -4.250   0.1607   0.01483   0.00737  -0.1315   0.7862   0.0245
  -4.000   0.1886   0.01420   0.00663  -0.1316   0.7698   0.0277
  -3.750   0.2167   0.01381   0.00607  -0.1315   0.7540   0.0318
  -3.500   0.2451   0.01331   0.00538  -0.1315   0.7395   0.0363
  -3.250   0.2732   0.01296   0.00484  -0.1314   0.7254   0.0440
  -3.000   0.3014   0.01254   0.00432  -0.1313   0.7115   0.0575
  -2.750   0.3290   0.01196   0.00404  -0.1314   0.6965   0.1453
  -2.500   0.3564   0.01201   0.00403  -0.1311   0.6804   0.1888
  -2.250   0.3837   0.01207   0.00395  -0.1308   0.6654   0.2047
  -2.000   0.4111   0.01214   0.00388  -0.1305   0.6516   0.2183
  -1.750   0.4384   0.01224   0.00383  -0.1301   0.6372   0.2320
  -1.250   0.4924   0.01234   0.00373  -0.1295   0.6075   0.2508
  -1.000   0.5194   0.01237   0.00365  -0.1291   0.5924   0.2567
  -0.750   0.5463   0.01243   0.00358  -0.1288   0.5779   0.2631
  -0.500   0.5733   0.01245   0.00356  -0.1285   0.5648   0.2696
  -0.250   0.6004   0.01252   0.00353  -0.1282   0.5524   0.2778
   0.000   0.6273   0.01256   0.00354  -0.1279   0.5399   0.2849
   0.250   0.6541   0.01263   0.00354  -0.1276   0.5268   0.2923
   0.500   0.6807   0.01269   0.00357  -0.1273   0.5123   0.2988
   0.750   0.7072   0.01278   0.00360  -0.1269   0.4948   0.3063
   1.000   0.7334   0.01287   0.00365  -0.1265   0.4734   0.3146
   1.250   0.7591   0.01300   0.00371  -0.1261   0.4459   0.3253
   1.500   0.7837   0.01322   0.00378  -0.1255   0.4085   0.3380
   2.000   0.8320   0.01377   0.00411  -0.1242   0.3608   0.3766
   2.250   0.8568   0.01398   0.00434  -0.1237   0.3490   0.4165
   2.500   0.8819   0.01408   0.00456  -0.1233   0.3397   0.4893
   3.000   0.9258   0.01368   0.00492  -0.1206   0.3255   1.0000
   3.250   0.9509   0.01403   0.00515  -0.1201   0.3193   1.0000
   3.500   0.9771   0.01425   0.00536  -0.1198   0.3146   1.0000
   3.750   1.0028   0.01452   0.00561  -0.1194   0.3094   1.0000
   4.000   1.0275   0.01486   0.00588  -0.1189   0.3038   1.0000
   4.250   1.0537   0.01507   0.00611  -0.1186   0.2978   1.0000
   4.500   1.0789   0.01535   0.00639  -0.1182   0.2921   1.0000
   4.750   1.1039   0.01565   0.00667  -0.1177   0.2877   1.0000
   5.000   1.1298   0.01585   0.00694  -0.1173   0.2832   1.0000
   5.250   1.1551   0.01611   0.00722  -0.1169   0.2778   1.0000
   5.500   1.1796   0.01641   0.00754  -0.1164   0.2727   1.0000
   5.750   1.2052   0.01662   0.00784  -0.1160   0.2675   1.0000
   6.000   1.2300   0.01689   0.00815  -0.1155   0.2622   1.0000
   6.250   1.2545   0.01717   0.00850  -0.1150   0.2572   1.0000
   6.500   1.2794   0.01742   0.00884  -0.1145   0.2505   1.0000
   6.750   1.3033   0.01772   0.00919  -0.1139   0.2427   1.0000
   7.000   1.3269   0.01803   0.00953  -0.1133   0.2267   1.0000
   7.250   1.3393   0.01924   0.01022  -0.1112   0.1552   1.0000
   7.500   1.3548   0.02030   0.01115  -0.1095   0.1299   1.0000
   7.750   1.3714   0.02120   0.01197  -0.1080   0.1107   1.0000
   8.000   1.3842   0.02236   0.01294  -0.1060   0.0688   1.0000
   8.250   1.3963   0.02349   0.01399  -0.1038   0.0592   1.0000
   8.500   1.4094   0.02445   0.01501  -0.1018   0.0545   1.0000
   8.750   1.4236   0.02518   0.01585  -0.0998   0.0502   1.0000
   9.000   1.4356   0.02601   0.01678  -0.0976   0.0458   1.0000
   9.250   1.4486   0.02681   0.01770  -0.0955   0.0404   1.0000
   9.500   1.4566   0.02795   0.01877  -0.0930   0.0191   1.0000
   9.750   1.4606   0.02944   0.02029  -0.0901   0.0161   1.0000
  10.000   1.4667   0.03085   0.02182  -0.0877   0.0144   1.0000
  10.250   1.4727   0.03233   0.02345  -0.0855   0.0134   1.0000
  10.500   1.4780   0.03395   0.02524  -0.0836   0.0127   1.0000
  10.750   1.4811   0.03585   0.02732  -0.0817   0.0119   1.0000
  11.000   1.4823   0.03806   0.02969  -0.0801   0.0112   1.0000
  11.250   1.4812   0.04062   0.03243  -0.0787   0.0107   1.0000
  11.500   1.4784   0.04352   0.03551  -0.0776   0.0104   1.0000
  11.750   1.4731   0.04685   0.03901  -0.0768   0.0101   1.0000
  12.000   1.4650   0.05070   0.04304  -0.0764   0.0098   1.0000
  12.250   1.4547   0.05503   0.04760  -0.0764   0.0096   1.0000
  12.500   1.4431   0.05971   0.05244  -0.0766   0.0095   1.0000
  12.750   1.4335   0.06428   0.05717  -0.0771   0.0094   1.0000
  13.000   1.4252   0.06879   0.06183  -0.0777   0.0093   1.0000
  13.250   1.4159   0.07353   0.06672  -0.0785   0.0092   1.0000
  13.500   1.4066   0.07842   0.07176  -0.0794   0.0091   1.0000
  13.750   1.3974   0.08338   0.07686  -0.0805   0.0089   1.0000
  14.000   1.3884   0.08840   0.08200  -0.0816   0.0088   1.0000
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