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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 50,000
Max Cl/Cd: 29.8 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe528-il-50000-n5.txt
Download as CSV file: xf-goe528-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2386   0.12332   0.11691  -0.0360   1.0000   0.1048
  -9.500  -0.2469   0.12225   0.11595  -0.0337   1.0000   0.1066
  -9.250  -0.2578   0.12146   0.11527  -0.0315   1.0000   0.1089
  -9.000  -0.2553   0.11980   0.11364  -0.0381   0.9909   0.1134
  -8.750  -0.2576   0.11867   0.11256  -0.0462   0.9779   0.1145
  -8.500  -0.2133   0.11043   0.10426  -0.0440   0.9768   0.1201
  -8.250  -0.1977   0.10707   0.10089  -0.0476   0.9678   0.1248
  -8.000  -0.1970   0.10534   0.09919  -0.0535   0.9550   0.1297
  -7.750  -0.2031   0.10404   0.09793  -0.0616   0.9389   0.1310
  -7.500  -0.1660   0.09740   0.09126  -0.0593   0.9375   0.1343
  -7.250  -0.1460   0.09399   0.08782  -0.0615   0.9297   0.1413
  -7.000  -0.1522   0.09265   0.08647  -0.0719   0.9124   0.1477
  -6.750  -0.1252   0.08762   0.08147  -0.0691   0.9078   0.1518
  -6.500  -0.1003   0.08379   0.07759  -0.0730   0.9017   0.1569
  -6.000  -0.0802   0.06980   0.06311  -0.0942   0.8749   0.0846
  -5.750  -0.0542   0.06573   0.05887  -0.0980   0.8683   0.0834
  -5.500  -0.0414   0.06265   0.05569  -0.0991   0.8570   0.0830
  -5.250  -0.0140   0.05867   0.05153  -0.1028   0.8507   0.0819
  -5.000  -0.0004   0.05582   0.04854  -0.1034   0.8389   0.0806
  -4.750   0.0304   0.05168   0.04408  -0.1074   0.8331   0.0791
  -4.500   0.0453   0.04901   0.04115  -0.1077   0.8213   0.0787
  -4.250   0.0759   0.04570   0.03739  -0.1105   0.8148   0.0800
  -4.000   0.0956   0.04338   0.03468  -0.1107   0.8040   0.0808
  -3.750   0.1267   0.04070   0.03153  -0.1122   0.7975   0.0808
  -3.500   0.1481   0.03892   0.02937  -0.1118   0.7873   0.0810
  -3.250   0.1833   0.03673   0.02667  -0.1133   0.7819   0.0819
  -3.000   0.2031   0.03566   0.02515  -0.1121   0.7707   0.0837
  -2.750   0.2379   0.03404   0.02332  -0.1133   0.7656   0.0866
  -2.500   0.2564   0.03338   0.02250  -0.1118   0.7544   0.0883
  -2.250   0.2920   0.03208   0.02090  -0.1126   0.7491   0.0906
  -2.000   0.3117   0.03160   0.02024  -0.1112   0.7382   0.0927
  -1.750   0.3471   0.03065   0.01896  -0.1119   0.7328   0.0976
  -1.500   0.3663   0.03035   0.01862  -0.1104   0.7223   0.1021
  -1.250   0.4012   0.02958   0.01768  -0.1110   0.7166   0.1089
  -1.000   0.4226   0.02944   0.01739  -0.1098   0.7069   0.1151
  -0.750   0.4548   0.02882   0.01670  -0.1102   0.7006   0.1295
  -0.500   0.4769   0.02865   0.01658  -0.1093   0.6916   0.1489
  -0.250   0.5067   0.02791   0.01620  -0.1095   0.6850   0.2126
   0.000   0.5459   0.02557   0.01602  -0.1111   0.6786   1.0000
   0.250   0.5686   0.02594   0.01602  -0.1101   0.6700   1.0000
   0.500   0.6000   0.02599   0.01569  -0.1102   0.6643   1.0000
   0.750   0.6166   0.02662   0.01613  -0.1085   0.6546   1.0000
   1.000   0.6495   0.02659   0.01581  -0.1088   0.6494   1.0000
   1.250   0.6638   0.02734   0.01643  -0.1069   0.6395   1.0000
   1.500   0.6949   0.02740   0.01626  -0.1070   0.6340   1.0000
   1.750   0.7108   0.02811   0.01686  -0.1054   0.6249   1.0000
   2.000   0.7392   0.02827   0.01686  -0.1052   0.6188   1.0000
   2.250   0.7586   0.02886   0.01734  -0.1040   0.6110   1.0000
   2.500   0.7827   0.02923   0.01759  -0.1033   0.6038   1.0000
   2.750   0.8108   0.02943   0.01766  -0.1030   0.5980   1.0000
   3.000   0.8253   0.03026   0.01845  -0.1013   0.5892   1.0000
   3.250   0.8588   0.03019   0.01825  -0.1017   0.5842   1.0000
   3.500   0.8679   0.03130   0.01937  -0.0994   0.5748   1.0000
   3.750   0.8980   0.03140   0.01938  -0.0993   0.5693   1.0000
   4.000   0.9117   0.03231   0.02028  -0.0976   0.5609   1.0000
   4.250   0.9361   0.03269   0.02062  -0.0969   0.5543   1.0000
   4.500   0.9618   0.03302   0.02090  -0.0965   0.5482   1.0000
   4.750   0.9729   0.03405   0.02195  -0.0944   0.5393   1.0000
   5.000   1.0091   0.03386   0.02169  -0.0950   0.5346   1.0000
   5.250   1.0084   0.03550   0.02341  -0.0918   0.5245   1.0000
   5.500   1.0412   0.03544   0.02331  -0.0920   0.5191   1.0000
   5.750   1.0433   0.03697   0.02490  -0.0891   0.5099   1.0000
   6.000   1.0703   0.03718   0.02512  -0.0887   0.5035   1.0000
   6.250   1.0792   0.03835   0.02634  -0.0866   0.4955   1.0000
   6.500   1.0936   0.03919   0.02721  -0.0849   0.4880   1.0000
   6.750   1.1296   0.03898   0.02700  -0.0855   0.4828   1.0000
   7.000   1.1102   0.04154   0.02967  -0.0805   0.4723   1.0000
   7.250   1.1538   0.04085   0.02898  -0.0817   0.4679   1.0000
   7.500   1.1217   0.04444   0.03268  -0.0762   0.4563   1.0000
   7.750   1.1624   0.04369   0.03196  -0.0768   0.4520   1.0000
   8.000   1.1271   0.04809   0.03648  -0.0723   0.4400   1.0000
   8.250   1.1664   0.04721   0.03563  -0.0724   0.4360   1.0000
   8.500   1.1282   0.05252   0.04105  -0.0689   0.4233   1.0000
   8.750   1.1663   0.05149   0.04006  -0.0686   0.4199   1.0000
   9.250   1.1049   0.06287   0.05162  -0.0654   0.3952   1.0000
   9.500   1.1227   0.06366   0.05248  -0.0645   0.3900   1.0000
   9.750   1.1571   0.06258   0.05150  -0.0636   0.3875   1.0000
  10.250   1.1403   0.07052   0.05959  -0.0625   0.3702   1.0000
  10.750   1.1345   0.07770   0.06694  -0.0620   0.3551   1.0000
  11.250   1.0666   0.09481   0.08418  -0.0650   0.3314   1.0000
  11.500   1.0805   0.09635   0.08582  -0.0645   0.3273   1.0000
  11.750   1.1035   0.09651   0.08611  -0.0636   0.3249   1.0000
  12.000   1.0624   0.10663   0.09626  -0.0663   0.3137   1.0000
  12.250   1.0775   0.10820   0.09796  -0.0660   0.3107   1.0000
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