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GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 500,000
Max Cl/Cd: 120.6 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe547-il-500000.txt
Download as CSV file: xf-goe547-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2428   0.08542   0.08323  -0.0598   0.9882   0.0332
  -9.500  -0.2483   0.07783   0.07565  -0.0671   0.9861   0.0359
  -9.250  -0.2461   0.07132   0.06914  -0.0722   0.9846   0.0361
  -9.000  -0.2554   0.06374   0.06158  -0.0750   0.9810   0.0370
  -8.750  -0.2425   0.06100   0.05883  -0.0765   0.9776   0.0377
  -8.500  -0.2306   0.05740   0.05522  -0.0793   0.9749   0.0384
  -8.250  -0.2194   0.05316   0.05098  -0.0834   0.9727   0.0396
  -8.000  -0.2205   0.04786   0.04569  -0.0881   0.9654   0.0409
  -7.750  -0.3206   0.03581   0.03265  -0.1150   0.9550   0.0348
  -7.500  -0.3096   0.02895   0.02520  -0.1175   0.9492   0.0337
  -7.250  -0.2839   0.02477   0.02051  -0.1198   0.9468   0.0343
  -7.000  -0.2582   0.02209   0.01743  -0.1207   0.9433   0.0348
  -6.750  -0.2354   0.02031   0.01536  -0.1204   0.9377   0.0352
  -6.500  -0.2023   0.02002   0.01486  -0.1216   0.9348   0.0361
  -6.250  -0.1739   0.01708   0.01155  -0.1228   0.9320   0.0366
  -6.000  -0.1495   0.01548   0.00977  -0.1225   0.9265   0.0372
  -5.750  -0.1210   0.01438   0.00857  -0.1229   0.9217   0.0380
  -5.500  -0.0889   0.01369   0.00781  -0.1240   0.9183   0.0392
  -5.250  -0.0611   0.01310   0.00715  -0.1241   0.9132   0.0401
  -5.000  -0.0341   0.01249   0.00646  -0.1240   0.9075   0.0407
  -4.750  -0.0033   0.01191   0.00580  -0.1246   0.9031   0.0415
  -4.500   0.0217   0.01147   0.00529  -0.1240   0.8967   0.0423
  -4.250   0.0488   0.01105   0.00482  -0.1239   0.8910   0.0431
  -4.000   0.0783   0.01070   0.00438  -0.1242   0.8863   0.0441
  -3.750   0.1023   0.01045   0.00410  -0.1233   0.8794   0.0451
  -3.500   0.1291   0.00996   0.00354  -0.1231   0.8738   0.0474
  -3.250   0.1547   0.00972   0.00329  -0.1226   0.8676   0.0498
  -3.000   0.1812   0.00953   0.00307  -0.1223   0.8613   0.0527
  -2.750   0.2095   0.00932   0.00282  -0.1223   0.8561   0.0579
  -2.500   0.2340   0.00911   0.00265  -0.1215   0.8489   0.0706
  -2.250   0.2614   0.00885   0.00241  -0.1214   0.8431   0.0953
  -2.000   0.2847   0.00843   0.00230  -0.1206   0.8361   0.1793
  -1.750   0.3109   0.00823   0.00223  -0.1203   0.8297   0.2330
  -1.500   0.3367   0.00805   0.00217  -0.1199   0.8231   0.2792
  -1.250   0.3617   0.00785   0.00213  -0.1193   0.8159   0.3373
  -1.000   0.3876   0.00766   0.00212  -0.1190   0.8094   0.4036
  -0.750   0.4118   0.00749   0.00213  -0.1182   0.8018   0.4713
  -0.500   0.4376   0.00736   0.00213  -0.1177   0.7951   0.5316
  -0.250   0.4612   0.00722   0.00215  -0.1167   0.7869   0.5884
   0.000   0.4848   0.00705   0.00215  -0.1157   0.7785   0.6564
   0.250   0.5064   0.00679   0.00213  -0.1142   0.7692   0.7368
   0.500   0.5719   0.00638   0.00220  -0.1220   0.7588   0.9641
   1.000   0.6527   0.00649   0.00214  -0.1275   0.7334   1.0000
   1.250   0.6755   0.00657   0.00213  -0.1263   0.7224   1.0000
   1.500   0.6980   0.00664   0.00216  -0.1251   0.7112   1.0000
   1.750   0.7214   0.00672   0.00220  -0.1241   0.7021   1.0000
   2.000   0.7450   0.00682   0.00224  -0.1231   0.6936   1.0000
   2.250   0.7684   0.00691   0.00231  -0.1221   0.6846   1.0000
   2.500   0.7920   0.00702   0.00238  -0.1212   0.6763   1.0000
   2.750   0.8152   0.00712   0.00246  -0.1201   0.6670   1.0000
   3.000   0.8379   0.00723   0.00254  -0.1189   0.6561   1.0000
   3.250   0.8599   0.00736   0.00263  -0.1176   0.6435   1.0000
   3.500   0.8820   0.00750   0.00272  -0.1163   0.6314   1.0000
   3.750   0.9048   0.00762   0.00284  -0.1152   0.6211   1.0000
   4.000   0.9275   0.00775   0.00296  -0.1141   0.6104   1.0000
   4.250   0.9495   0.00790   0.00309  -0.1128   0.5975   1.0000
   4.500   0.9708   0.00805   0.00322  -0.1114   0.5829   1.0000
   4.750   0.9909   0.00823   0.00336  -0.1097   0.5632   1.0000
   5.000   1.0089   0.00846   0.00351  -0.1076   0.5356   1.0000
   5.250   1.0235   0.00879   0.00369  -0.1048   0.4953   1.0000
   5.500   1.0327   0.00936   0.00397  -0.1010   0.4352   1.0000
   5.750   1.0411   0.01007   0.00436  -0.0973   0.3745   1.0000
   6.000   1.0523   0.01072   0.00477  -0.0941   0.3276   1.0000
   6.250   1.0655   0.01127   0.00517  -0.0914   0.2936   1.0000
   6.500   1.0785   0.01178   0.00554  -0.0886   0.2640   1.0000
   6.750   1.0903   0.01235   0.00595  -0.0857   0.2320   1.0000
   7.000   1.1036   0.01288   0.00635  -0.0830   0.2033   1.0000
   7.250   1.1143   0.01356   0.00682  -0.0800   0.1595   1.0000
   7.500   1.1236   0.01434   0.00739  -0.0769   0.1256   1.0000
   7.750   1.1360   0.01499   0.00795  -0.0743   0.1082   1.0000
   8.000   1.1504   0.01555   0.00847  -0.0721   0.0930   1.0000
   8.250   1.1603   0.01637   0.00909  -0.0692   0.0614   1.0000
   8.500   1.1692   0.01728   0.00989  -0.0662   0.0407   1.0000
   8.750   1.1788   0.01819   0.01070  -0.0634   0.0276   1.0000
   9.000   1.1912   0.01895   0.01146  -0.0611   0.0239   1.0000
   9.250   1.2028   0.01977   0.01233  -0.0587   0.0217   1.0000
   9.500   1.2156   0.02053   0.01315  -0.0566   0.0204   1.0000
   9.750   1.2263   0.02143   0.01409  -0.0543   0.0190   1.0000
  10.000   1.2335   0.02259   0.01531  -0.0516   0.0179   1.0000
  10.250   1.2407   0.02378   0.01658  -0.0491   0.0173   1.0000
  10.500   1.2504   0.02484   0.01773  -0.0469   0.0168   1.0000
  10.750   1.2592   0.02597   0.01895  -0.0448   0.0164   1.0000
  11.000   1.2666   0.02726   0.02031  -0.0426   0.0158   1.0000
  11.250   1.2736   0.02861   0.02173  -0.0405   0.0154   1.0000
  11.500   1.2805   0.03001   0.02320  -0.0386   0.0151   1.0000
  11.750   1.2861   0.03155   0.02480  -0.0366   0.0146   1.0000
  12.000   1.2893   0.03337   0.02668  -0.0345   0.0142   1.0000
  12.250   1.2905   0.03548   0.02888  -0.0324   0.0138   1.0000
  12.500   1.2937   0.03754   0.03104  -0.0305   0.0134   1.0000
  12.750   1.3013   0.03917   0.03278  -0.0291   0.0132   1.0000
  13.000   1.3093   0.04070   0.03442  -0.0279   0.0129   1.0000
  13.250   1.3153   0.04259   0.03642  -0.0265   0.0127   1.0000
  13.500   1.3210   0.04449   0.03843  -0.0252   0.0124   1.0000
  13.750   1.3263   0.04651   0.04056  -0.0241   0.0122   1.0000
  14.000   1.3306   0.04868   0.04285  -0.0229   0.0119   1.0000
  14.250   1.3345   0.05098   0.04528  -0.0219   0.0119   1.0000
  14.500   1.3373   0.05340   0.04782  -0.0210   0.0117   1.0000
  14.750   1.3392   0.05593   0.05047  -0.0202   0.0115   1.0000
  15.000   1.3399   0.05873   0.05341  -0.0196   0.0114   1.0000
  15.250   1.3387   0.06168   0.05647  -0.0192   0.0112   1.0000
  15.500   1.3362   0.06501   0.05997  -0.0188   0.0112   1.0000
  15.750   1.3329   0.06844   0.06353  -0.0188   0.0110   1.0000
  16.000   1.3276   0.07228   0.06752  -0.0190   0.0110   1.0000
  16.250   1.3203   0.07649   0.07189  -0.0195   0.0109   1.0000
  16.500   1.3117   0.08104   0.07661  -0.0204   0.0109   1.0000
  16.750   1.3010   0.08606   0.08180  -0.0217   0.0108   1.0000
  17.000   1.2895   0.09137   0.08728  -0.0234   0.0108   1.0000
  17.250   1.2759   0.09722   0.09329  -0.0255   0.0107   1.0000
  17.500   1.2600   0.10383   0.10010  -0.0285   0.0108   1.0000
  17.750   1.2447   0.11062   0.10708  -0.0319   0.0108   1.0000
  18.000   1.2297   0.11760   0.11421  -0.0357   0.0108   1.0000
  18.250   1.2135   0.12509   0.12185  -0.0400   0.0107   1.0000
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