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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.31 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe301-il-1000000-n5.txt
Download as CSV file: xf-goe301-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1457   0.08727   0.08535  -0.0704   0.9100   0.0106
  -9.000  -0.1380   0.08472   0.08268  -0.0716   0.8838   0.0109
  -8.750  -0.1322   0.08181   0.07965  -0.0729   0.8555   0.0113
  -8.500  -0.1381   0.07601   0.07372  -0.0763   0.8185   0.0125
  -8.250  -0.1300   0.07434   0.07179  -0.0771   0.7604   0.0127
  -8.000  -0.1174   0.07235   0.06966  -0.0791   0.7285   0.0128
  -7.750  -0.1026   0.06998   0.06720  -0.0820   0.7112   0.0131
  -7.250  -0.0722   0.05863   0.05573  -0.0975   0.6907   0.0153
  -7.000  -0.0505   0.05646   0.05349  -0.1007   0.6807   0.0155
  -6.750  -0.0277   0.05424   0.05122  -0.1040   0.6721   0.0158
  -6.500  -0.0040   0.05185   0.04876  -0.1075   0.6636   0.0162
  -6.250   0.0282   0.04151   0.03821  -0.1212   0.6584   0.0185
  -6.000   0.0544   0.03976   0.03638  -0.1234   0.6515   0.0187
  -5.750   0.0808   0.03797   0.03450  -0.1254   0.6449   0.0190
  -5.500   0.1135   0.01550   0.01056  -0.1395   0.6429   0.0236
  -5.250   0.1403   0.01386   0.00861  -0.1399   0.6364   0.0244
  -5.000   0.1674   0.01278   0.00727  -0.1400   0.6297   0.0248
  -4.750   0.1951   0.01207   0.00639  -0.1401   0.6239   0.0252
  -4.500   0.2229   0.01154   0.00571  -0.1401   0.6181   0.0255
  -4.250   0.2507   0.01115   0.00519  -0.1400   0.6123   0.0257
  -4.000   0.2788   0.01081   0.00475  -0.1400   0.6067   0.0259
  -3.750   0.3068   0.01051   0.00434  -0.1400   0.6000   0.0261
  -3.500   0.3345   0.01008   0.00381  -0.1399   0.5938   0.0267
  -3.250   0.3627   0.00989   0.00358  -0.1399   0.5878   0.0272
  -3.000   0.3907   0.00974   0.00339  -0.1398   0.5813   0.0276
  -2.750   0.4188   0.00958   0.00318  -0.1398   0.5753   0.0280
  -2.500   0.4469   0.00944   0.00299  -0.1397   0.5676   0.0284
  -2.250   0.4748   0.00932   0.00281  -0.1396   0.5600   0.0288
  -2.000   0.5028   0.00919   0.00264  -0.1396   0.5516   0.0292
  -1.750   0.5307   0.00910   0.00249  -0.1395   0.5437   0.0297
  -1.500   0.5585   0.00902   0.00236  -0.1394   0.5337   0.0301
  -1.250   0.5863   0.00898   0.00225  -0.1393   0.5225   0.0305
  -1.000   0.6137   0.00897   0.00217  -0.1391   0.5085   0.0309
  -0.750   0.6409   0.00894   0.00206  -0.1389   0.4914   0.0318
  -0.500   0.6678   0.00900   0.00204  -0.1387   0.4730   0.0329
  -0.250   0.6948   0.00906   0.00203  -0.1385   0.4575   0.0339
   0.000   0.7220   0.00912   0.00203  -0.1383   0.4453   0.0349
   0.250   0.7491   0.00919   0.00203  -0.1381   0.4331   0.0360
   0.500   0.7761   0.00927   0.00205  -0.1379   0.4201   0.0370
   0.750   0.8034   0.00931   0.00207  -0.1377   0.4099   0.0395
   1.000   0.8305   0.00939   0.00212  -0.1375   0.4022   0.0421
   1.250   0.8583   0.00942   0.00215  -0.1375   0.3970   0.0452
   1.500   0.8857   0.00948   0.00221  -0.1374   0.3910   0.0499
   1.750   0.9129   0.00956   0.00228  -0.1372   0.3852   0.0540
   2.000   0.9403   0.00961   0.00234  -0.1371   0.3793   0.0585
   2.250   0.9673   0.00971   0.00242  -0.1369   0.3723   0.0617
   2.500   0.9945   0.00978   0.00249  -0.1368   0.3666   0.0667
   2.750   1.0216   0.00986   0.00257  -0.1367   0.3606   0.0713
   3.250   1.0755   0.01003   0.00275  -0.1364   0.3489   0.0869
   3.500   1.1023   0.01001   0.00291  -0.1363   0.3416   0.2013
   4.000   1.1514   0.00902   0.00337  -0.1355   0.3250   1.0000
   4.250   1.1779   0.00918   0.00350  -0.1353   0.3177   1.0000
   4.500   1.2037   0.00939   0.00364  -0.1349   0.3086   1.0000
   4.750   1.2295   0.00959   0.00379  -0.1346   0.2987   1.0000
   5.000   1.2548   0.00983   0.00397  -0.1342   0.2880   1.0000
   5.250   1.2798   0.01008   0.00416  -0.1338   0.2776   1.0000
   5.500   1.3047   0.01033   0.00436  -0.1334   0.2666   1.0000
   5.750   1.3292   0.01060   0.00457  -0.1328   0.2558   1.0000
   6.000   1.3535   0.01088   0.00481  -0.1323   0.2469   1.0000
   6.250   1.3782   0.01112   0.00502  -0.1318   0.2388   1.0000
   6.500   1.4020   0.01141   0.00527  -0.1312   0.2307   1.0000
   6.750   1.4265   0.01165   0.00550  -0.1307   0.2244   1.0000
   7.000   1.4499   0.01195   0.00577  -0.1301   0.2174   1.0000
   7.250   1.4740   0.01219   0.00601  -0.1295   0.2120   1.0000
   7.500   1.4972   0.01248   0.00629  -0.1289   0.2056   1.0000
   7.750   1.5200   0.01279   0.00658  -0.1281   0.1987   1.0000
   8.000   1.5405   0.01324   0.00695  -0.1270   0.1845   1.0000
   8.250   1.5575   0.01390   0.00746  -0.1253   0.1598   1.0000
   8.500   1.5728   0.01463   0.00805  -0.1234   0.1365   1.0000
   8.750   1.5906   0.01515   0.00852  -0.1218   0.1265   1.0000
   9.000   1.6077   0.01564   0.00897  -0.1201   0.1194   1.0000
   9.250   1.6258   0.01601   0.00936  -0.1185   0.1160   1.0000
   9.500   1.6427   0.01644   0.00981  -0.1168   0.1123   1.0000
   9.750   1.6586   0.01693   0.01030  -0.1150   0.1082   1.0000
  10.000   1.6751   0.01740   0.01079  -0.1133   0.1042   1.0000
  10.250   1.6921   0.01784   0.01126  -0.1117   0.1010   1.0000
  10.500   1.7062   0.01844   0.01186  -0.1097   0.0954   1.0000
  10.750   1.7201   0.01907   0.01249  -0.1078   0.0900   1.0000
  11.000   1.7216   0.02043   0.01368  -0.1042   0.0651   1.0000
  11.250   1.7216   0.02196   0.01513  -0.1005   0.0488   1.0000
  11.500   1.7255   0.02332   0.01648  -0.0977   0.0394   1.0000
  11.750   1.7260   0.02500   0.01812  -0.0947   0.0286   1.0000
  12.000   1.7241   0.02695   0.02004  -0.0917   0.0181   1.0000
  12.250   1.7294   0.02848   0.02161  -0.0897   0.0153   1.0000
  12.500   1.7350   0.03004   0.02321  -0.0879   0.0137   1.0000
  12.750   1.7409   0.03166   0.02489  -0.0863   0.0125   1.0000
  13.000   1.7468   0.03336   0.02665  -0.0849   0.0116   1.0000
  13.250   1.7508   0.03529   0.02865  -0.0836   0.0108   1.0000
  13.500   1.7535   0.03745   0.03088  -0.0824   0.0100   1.0000
  13.750   1.7580   0.03951   0.03302  -0.0815   0.0096   1.0000
  14.000   1.7612   0.04179   0.03537  -0.0806   0.0092   1.0000
  14.250   1.7627   0.04428   0.03795  -0.0799   0.0088   1.0000
  14.500   1.7630   0.04698   0.04072  -0.0792   0.0084   1.0000
  14.750   1.7621   0.04989   0.04370  -0.0786   0.0081   1.0000
  15.000   1.7593   0.05308   0.04698  -0.0781   0.0077   1.0000
  15.250   1.7572   0.05622   0.05021  -0.0778   0.0075   1.0000
  15.500   1.7546   0.05947   0.05356  -0.0775   0.0073   1.0000
  15.750   1.7510   0.06292   0.05710  -0.0773   0.0071   1.0000
  16.000   1.7464   0.06657   0.06084  -0.0773   0.0069   1.0000
  16.250   1.7405   0.07042   0.06478  -0.0774   0.0067   1.0000
  16.500   1.7337   0.07446   0.06892  -0.0776   0.0065   1.0000
  16.750   1.7262   0.07870   0.07325  -0.0779   0.0063   1.0000
  17.000   1.7177   0.08315   0.07779  -0.0784   0.0062   1.0000
  17.250   1.7081   0.08781   0.08255  -0.0791   0.0060   1.0000
  17.500   1.6972   0.09271   0.08756  -0.0799   0.0059   1.0000
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