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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 50,000
Max Cl/Cd: 30.29 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe176-il-50000.txt
Download as CSV file: xf-goe176-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2781   0.10405   0.09772  -0.0233   1.0000   0.2010
  -7.500  -0.2817   0.10243   0.09621  -0.0227   1.0000   0.2066
  -7.250  -0.3068   0.10364   0.09768  -0.0219   1.0000   0.2095
  -7.000  -0.2923   0.09845   0.09253  -0.0205   1.0000   0.2128
  -6.750  -0.2882   0.09563   0.08979  -0.0188   1.0000   0.2179
  -6.500  -0.3010   0.09497   0.08931  -0.0182   1.0000   0.2233
  -6.250  -0.3177   0.09465   0.08920  -0.0191   1.0000   0.2257
  -6.000  -0.3085   0.09035   0.08494  -0.0150   1.0000   0.2295
  -5.750  -0.3135   0.08863   0.08333  -0.0131   1.0000   0.2350
  -5.500  -0.3319   0.08938   0.08421  -0.0169   1.0000   0.2404
  -5.250  -0.3291   0.08541   0.08032  -0.0118   1.0000   0.2437
  -5.000  -0.3305   0.08338   0.07837  -0.0100   1.0000   0.2502
  -4.750  -0.3335   0.08191   0.07696  -0.0138   1.0000   0.2569
  -4.500  -0.3321   0.07911   0.07423  -0.0103   1.0000   0.2616
  -4.250  -0.3245   0.07733   0.07245  -0.0163   1.0000   0.2716
  -4.000  -0.3209   0.07425   0.06943  -0.0139   1.0000   0.2745
  -3.750  -0.3113   0.07164   0.06681  -0.0151   1.0000   0.2799
  -3.500  -0.1834   0.05024   0.04415  -0.0610   1.0000   0.1353
  -3.250  -0.1405   0.04474   0.03816  -0.0686   1.0000   0.1339
  -3.000  -0.0888   0.03882   0.03139  -0.0771   1.0000   0.1348
  -2.750  -0.0493   0.03553   0.02749  -0.0814   1.0000   0.1403
  -2.500  -0.0198   0.03428   0.02591  -0.0832   1.0000   0.1531
  -2.250   0.0367   0.03335   0.02472  -0.0889   0.9903   0.1822
  -2.000   0.0957   0.03307   0.02451  -0.0942   0.9766   0.2730
  -1.750   0.1411   0.03332   0.02496  -0.0970   0.9622   0.3696
  -1.500   0.1905   0.03309   0.02467  -0.1007   0.9472   0.4336
  -1.250   0.2416   0.03231   0.02359  -0.1054   0.9313   0.4570
  -1.000   0.2907   0.03170   0.02271  -0.1096   0.9167   0.4775
  -0.750   0.3401   0.03119   0.02192  -0.1137   0.9031   0.4991
  -0.500   0.3898   0.03057   0.02113  -0.1174   0.8895   0.5222
  -0.250   0.4352   0.03002   0.02047  -0.1203   0.8749   0.5470
   0.000   0.4809   0.02938   0.01980  -0.1230   0.8602   0.5758
   0.250   0.5235   0.02862   0.01918  -0.1248   0.8452   0.6148
   0.500   0.5600   0.02757   0.01868  -0.1250   0.8298   0.6912
   0.750   0.6014   0.02676   0.01798  -0.1260   0.8130   1.0000
   1.000   0.6343   0.02703   0.01787  -0.1263   0.7917   1.0000
   1.250   0.6716   0.02696   0.01749  -0.1266   0.7723   1.0000
   1.500   0.7085   0.02681   0.01711  -0.1267   0.7537   1.0000
   1.750   0.7365   0.02707   0.01721  -0.1257   0.7315   1.0000
   2.000   0.7667   0.02721   0.01718  -0.1249   0.7110   1.0000
   2.250   0.7980   0.02731   0.01710  -0.1242   0.6927   1.0000
   2.500   0.8239   0.02781   0.01750  -0.1233   0.6740   1.0000
   2.750   0.8487   0.02850   0.01810  -0.1224   0.6571   1.0000
   3.000   0.8751   0.02917   0.01868  -0.1219   0.6435   1.0000
   3.250   0.9025   0.02980   0.01923  -0.1215   0.6318   1.0000
   3.500   0.9232   0.03099   0.02046  -0.1208   0.6192   1.0000
   3.750   0.9437   0.03226   0.02175  -0.1201   0.6082   1.0000
   4.000   0.9730   0.03281   0.02224  -0.1199   0.6005   1.0000
   4.250   0.9873   0.03476   0.02431  -0.1192   0.5907   1.0000
   4.500   1.0118   0.03591   0.02551  -0.1189   0.5842   1.0000
   4.750   1.0237   0.03817   0.02791  -0.1182   0.5757   1.0000
   5.000   1.0501   0.03912   0.02888  -0.1179   0.5697   1.0000
   5.250   1.0510   0.04257   0.03253  -0.1170   0.5616   1.0000
   5.500   1.0823   0.04304   0.03306  -0.1167   0.5562   1.0000
   5.750   1.0691   0.04778   0.03798  -0.1153   0.5466   1.0000
   6.000   1.0956   0.04819   0.03845  -0.1143   0.5372   1.0000
   6.250   1.1307   0.04749   0.03779  -0.1131   0.5266   1.0000
   6.500   1.1246   0.05107   0.04153  -0.1113   0.5150   1.0000
   6.750   1.1373   0.05274   0.04332  -0.1098   0.5046   1.0000
   7.000   1.1898   0.04996   0.04059  -0.1087   0.4933   1.0000
   7.250   1.2177   0.04966   0.04039  -0.1072   0.4809   1.0000
   7.500   1.1702   0.05799   0.04892  -0.1050   0.4722   1.0000
   7.750   1.2168   0.05516   0.04623  -0.1031   0.4579   1.0000
   8.000   1.2560   0.05336   0.04453  -0.1015   0.4447   1.0000
   8.250   1.3088   0.05082   0.04207  -0.1011   0.4343   1.0000
   8.500   1.2886   0.05556   0.04705  -0.0983   0.4239   1.0000
   8.750   1.2622   0.06113   0.05278  -0.0959   0.4140   1.0000
   9.000   1.3419   0.05626   0.04812  -0.0961   0.4052   1.0000
   9.250   1.2201   0.07176   0.06356  -0.0926   0.3944   1.0000
   9.500   1.1037   0.09245   0.08400  -0.0989   0.3830   1.0000
   9.750   1.1149   0.09455   0.08622  -0.0978   0.3733   1.0000
  10.000   1.1079   0.09951   0.09124  -0.0981   0.3649   1.0000
  10.250   1.0876   0.10659   0.09832  -0.0996   0.3584   1.0000
  10.500   1.0609   0.11475   0.10649  -0.1021   0.3550   1.0000
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