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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 500,000
Max Cl/Cd: 114.65 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe303-il-500000.txt
Download as CSV file: xf-goe303-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2828   0.12029   0.11791  -0.0363   1.0000   0.0220
 -10.500  -0.2908   0.11769   0.11534  -0.0380   1.0000   0.0222
 -10.250  -0.2984   0.11533   0.11302  -0.0381   1.0000   0.0222
 -10.000  -0.2943   0.11212   0.10984  -0.0360   1.0000   0.0224
  -9.750  -0.2946   0.11026   0.10802  -0.0335   1.0000   0.0225
  -9.500  -0.2912   0.10811   0.10589  -0.0327   0.9995   0.0227
  -9.250  -0.2754   0.10473   0.10250  -0.0357   0.9979   0.0231
  -9.000  -0.2595   0.10120   0.09897  -0.0393   0.9960   0.0237
  -8.750  -0.2433   0.09745   0.09522  -0.0434   0.9942   0.0245
  -8.500  -0.2296   0.09307   0.09084  -0.0492   0.9901   0.0261
  -8.250  -0.2169   0.08692   0.08468  -0.0621   0.9841   0.0265
  -8.000  -0.2032   0.08300   0.08077  -0.0628   0.9807   0.0268
  -7.750  -0.1832   0.08018   0.07794  -0.0643   0.9775   0.0272
  -7.500  -0.1607   0.07680   0.07456  -0.0689   0.9742   0.0278
  -7.250  -0.1387   0.07318   0.07093  -0.0742   0.9697   0.0287
  -7.000  -0.1178   0.06914   0.06687  -0.0804   0.9620   0.0301
  -6.750  -0.0873   0.06004   0.05765  -0.0978   0.9512   0.0318
  -6.500  -0.0696   0.05795   0.05555  -0.0980   0.9454   0.0322
  -6.250  -0.0513   0.05587   0.05345  -0.0989   0.9371   0.0328
  -6.000  -0.0287   0.05307   0.05058  -0.1019   0.9295   0.0338
  -5.750   0.0147   0.04552   0.04270  -0.1144   0.9186   0.0374
  -5.500   0.0300   0.04150   0.03862  -0.1158   0.9103   0.0381
  -5.250   0.0501   0.04012   0.03720  -0.1158   0.9009   0.0388
  -5.000   0.0726   0.03850   0.03551  -0.1164   0.8915   0.0399
  -4.750   0.1079   0.03144   0.02790  -0.1219   0.8825   0.0451
  -4.500   0.1298   0.03007   0.02651  -0.1219   0.8718   0.0458
  -4.250   0.1537   0.02889   0.02526  -0.1220   0.8617   0.0466
  -4.000   0.1790   0.02744   0.02368  -0.1223   0.8505   0.0483
  -3.750   0.2081   0.02364   0.01940  -0.1234   0.8385   0.0544
  -3.500   0.2332   0.02261   0.01831  -0.1234   0.8256   0.0555
  -3.250   0.2626   0.01593   0.01060  -0.1235   0.8142   0.0427
  -3.000   0.2896   0.01426   0.00857  -0.1232   0.8000   0.0421
  -2.750   0.3169   0.01312   0.00714  -0.1228   0.7850   0.0420
  -2.500   0.3441   0.01229   0.00606  -0.1225   0.7700   0.0420
  -2.250   0.3713   0.01171   0.00529  -0.1221   0.7546   0.0424
  -2.000   0.3983   0.01127   0.00468  -0.1217   0.7388   0.0428
  -1.500   0.4526   0.01075   0.00391  -0.1210   0.7092   0.0442
  -1.250   0.4796   0.01031   0.00339  -0.1208   0.6962   0.0455
  -1.000   0.5068   0.01005   0.00308  -0.1205   0.6841   0.0469
  -0.750   0.5341   0.00993   0.00290  -0.1203   0.6724   0.0485
  -0.500   0.5613   0.00984   0.00275  -0.1200   0.6601   0.0504
  -0.250   0.5888   0.00976   0.00262  -0.1198   0.6479   0.0526
   0.000   0.6161   0.00964   0.00249  -0.1196   0.6361   0.0579
   0.250   0.6433   0.00960   0.00242  -0.1193   0.6252   0.0689
   0.500   0.6708   0.00947   0.00239  -0.1192   0.6149   0.1082
   0.750   0.6982   0.00942   0.00242  -0.1191   0.6059   0.1489
   1.000   0.7254   0.00936   0.00246  -0.1190   0.5968   0.2043
   1.250   0.7442   0.00792   0.00268  -0.1176   0.5888   0.8365
   1.500   0.7798   0.00785   0.00266  -0.1190   0.5794   1.0000
   1.750   0.8071   0.00795   0.00271  -0.1188   0.5701   1.0000
   2.000   0.8339   0.00810   0.00275  -0.1186   0.5612   1.0000
   2.250   0.8611   0.00821   0.00282  -0.1184   0.5521   1.0000
   2.500   0.8880   0.00836   0.00289  -0.1181   0.5437   1.0000
   2.750   0.9149   0.00849   0.00297  -0.1179   0.5347   1.0000
   3.000   0.9417   0.00863   0.00306  -0.1176   0.5261   1.0000
   3.250   0.9683   0.00878   0.00317  -0.1174   0.5168   1.0000
   3.500   0.9950   0.00892   0.00327  -0.1171   0.5075   1.0000
   3.750   1.0211   0.00910   0.00339  -0.1168   0.4980   1.0000
   4.000   1.0476   0.00924   0.00351  -0.1165   0.4872   1.0000
   4.250   1.0737   0.00941   0.00365  -0.1162   0.4757   1.0000
   4.500   1.0993   0.00960   0.00379  -0.1158   0.4635   1.0000
   4.750   1.1247   0.00981   0.00395  -0.1153   0.4502   1.0000
   5.000   1.1498   0.01003   0.00413  -0.1148   0.4355   1.0000
   5.250   1.1746   0.01027   0.00432  -0.1143   0.4188   1.0000
   5.500   1.1989   0.01054   0.00453  -0.1137   0.3989   1.0000
   5.750   1.2215   0.01092   0.00479  -0.1128   0.3740   1.0000
   6.000   1.2433   0.01138   0.00510  -0.1119   0.3449   1.0000
   6.250   1.2649   0.01185   0.00544  -0.1109   0.3198   1.0000
   6.500   1.2867   0.01230   0.00579  -0.1099   0.3016   1.0000
   6.750   1.3087   0.01272   0.00615  -0.1090   0.2875   1.0000
   7.000   1.3308   0.01312   0.00651  -0.1081   0.2764   1.0000
   7.250   1.3524   0.01355   0.00689  -0.1071   0.2675   1.0000
   7.500   1.3751   0.01388   0.00724  -0.1063   0.2603   1.0000
   7.750   1.3960   0.01431   0.00764  -0.1053   0.2526   1.0000
   8.000   1.4183   0.01464   0.00800  -0.1044   0.2468   1.0000
   8.250   1.4396   0.01501   0.00839  -0.1034   0.2405   1.0000
   8.500   1.4597   0.01544   0.00882  -0.1023   0.2341   1.0000
   8.750   1.4811   0.01576   0.00919  -0.1013   0.2276   1.0000
   9.250   1.5200   0.01654   0.01001  -0.0987   0.2141   1.0000
   9.500   1.5359   0.01702   0.01049  -0.0968   0.2070   1.0000
   9.750   1.5548   0.01737   0.01090  -0.0954   0.2003   1.0000
  10.000   1.5705   0.01788   0.01141  -0.0936   0.1918   1.0000
  10.250   1.5885   0.01830   0.01187  -0.0922   0.1814   1.0000
  10.500   1.6037   0.01888   0.01243  -0.0904   0.1673   1.0000
  10.750   1.6148   0.01971   0.01316  -0.0881   0.1454   1.0000
  11.000   1.6195   0.02097   0.01424  -0.0851   0.1186   1.0000
  11.250   1.6233   0.02233   0.01551  -0.0821   0.1008   1.0000
  11.500   1.6296   0.02360   0.01675  -0.0796   0.0903   1.0000
  11.750   1.6370   0.02483   0.01799  -0.0773   0.0827   1.0000
  12.000   1.6426   0.02624   0.01941  -0.0750   0.0758   1.0000
  12.250   1.6513   0.02746   0.02068  -0.0732   0.0700   1.0000
  12.500   1.6561   0.02904   0.02227  -0.0712   0.0635   1.0000
  12.750   1.6616   0.03061   0.02386  -0.0694   0.0562   1.0000
  13.000   1.6640   0.03250   0.02575  -0.0675   0.0472   1.0000
  13.250   1.6624   0.03485   0.02807  -0.0655   0.0368   1.0000
  13.500   1.6588   0.03749   0.03070  -0.0637   0.0292   1.0000
  13.750   1.6554   0.04026   0.03350  -0.0622   0.0254   1.0000
  14.000   1.6532   0.04303   0.03635  -0.0610   0.0233   1.0000
  14.250   1.6477   0.04626   0.03965  -0.0600   0.0217   1.0000
  14.500   1.6451   0.04931   0.04282  -0.0593   0.0207   1.0000
  14.750   1.6420   0.05253   0.04615  -0.0587   0.0198   1.0000
  15.000   1.6365   0.05613   0.04986  -0.0584   0.0190   1.0000
  15.250   1.6282   0.06020   0.05403  -0.0583   0.0184   1.0000
  15.500   1.6166   0.06484   0.05879  -0.0584   0.0178   1.0000
  15.750   1.6050   0.06961   0.06368  -0.0588   0.0174   1.0000
  16.000   1.5976   0.07388   0.06808  -0.0592   0.0171   1.0000
  16.250   1.5887   0.07847   0.07280  -0.0598   0.0168   1.0000
  16.500   1.5788   0.08330   0.07775  -0.0606   0.0165   1.0000
  16.750   1.5678   0.08835   0.08293  -0.0616   0.0162   1.0000
  17.000   1.5564   0.09355   0.08825  -0.0627   0.0159   1.0000
  17.250   1.5448   0.09888   0.09369  -0.0640   0.0157   1.0000
  17.500   1.5331   0.10432   0.09924  -0.0655   0.0155   1.0000
  17.750   1.5210   0.10985   0.10488  -0.0672   0.0153   1.0000
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