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GOE 484 AIRFOIL (goe484-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 484 AIRFOIL (goe484-il)
Reynolds number: 500,000
Max Cl/Cd: 128 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe484-il-500000.txt
Download as CSV file: xf-goe484-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 484 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3719   0.11143   0.10909  -0.0296   1.0000   0.0211
  -9.250  -0.3772   0.10941   0.10711  -0.0289   1.0000   0.0212
  -9.000  -0.3839   0.10744   0.10518  -0.0278   1.0000   0.0212
  -8.750  -0.3825   0.10457   0.10232  -0.0290   0.9992   0.0212
  -8.500  -0.3684   0.09950   0.09724  -0.0296   0.9982   0.0216
  -8.250  -0.3502   0.09602   0.09375  -0.0323   0.9964   0.0219
  -8.000  -0.3308   0.09268   0.09041  -0.0359   0.9945   0.0224
  -7.750  -0.3143   0.08934   0.08706  -0.0397   0.9913   0.0229
  -7.500  -0.2967   0.08588   0.08360  -0.0442   0.9878   0.0240
  -7.250  -0.2683   0.08085   0.07855  -0.0562   0.9837   0.0261
  -7.000  -0.2437   0.07586   0.07353  -0.0663   0.9765   0.0264
  -6.750  -0.2125   0.07058   0.06822  -0.0759   0.9735   0.0265
  -6.500  -0.1948   0.06527   0.06289  -0.0797   0.9720   0.0272
  -6.250  -0.1751   0.06266   0.06027  -0.0819   0.9676   0.0276
  -6.000  -0.1514   0.05993   0.05752  -0.0853   0.9637   0.0284
  -5.750  -0.1190   0.05617   0.05372  -0.0922   0.9612   0.0300
  -5.500  -0.0583   0.04909   0.04646  -0.1098   0.9593   0.0331
  -5.250  -0.0165   0.04061   0.03779  -0.1217   0.9579   0.0340
  -5.000   0.0038   0.03876   0.03590  -0.1225   0.9523   0.0347
  -4.750   0.0334   0.03677   0.03387  -0.1252   0.9493   0.0357
  -4.500   0.0684   0.03394   0.03093  -0.1294   0.9469   0.0378
  -4.250   0.1150   0.02638   0.02280  -0.1377   0.9444   0.0433
  -4.000   0.1407   0.02529   0.02170  -0.1383   0.9401   0.0443
  -3.750   0.1667   0.02412   0.02046  -0.1389   0.9354   0.0460
  -3.500   0.2011   0.02079   0.01660  -0.1413   0.9321   0.0538
  -3.250   0.2310   0.01968   0.01553  -0.1425   0.9296   0.0555
  -3.000   0.2560   0.01905   0.01487  -0.1422   0.9244   0.0584
  -2.750   0.2846   0.01750   0.01303  -0.1428   0.9196   0.0670
  -2.500   0.3177   0.01263   0.00722  -0.1428   0.9161   0.0437
  -2.250   0.3463   0.01251   0.00700  -0.1426   0.9114   0.0423
  -2.000   0.3729   0.01127   0.00564  -0.1422   0.9059   0.0409
  -1.750   0.4021   0.01050   0.00476  -0.1424   0.9017   0.0404
  -1.500   0.4297   0.01005   0.00426  -0.1421   0.8966   0.0408
  -1.250   0.4567   0.00961   0.00378  -0.1417   0.8906   0.0410
  -1.000   0.4858   0.00914   0.00326  -0.1418   0.8857   0.0409
  -0.750   0.5117   0.00883   0.00294  -0.1412   0.8787   0.0410
  -0.500   0.5398   0.00855   0.00263  -0.1410   0.8724   0.0415
  -0.250   0.5667   0.00835   0.00243  -0.1406   0.8655   0.0421
   0.000   0.5941   0.00810   0.00215  -0.1403   0.8583   0.0437
   0.250   0.6209   0.00797   0.00201  -0.1398   0.8494   0.0458
   0.500   0.6482   0.00787   0.00188  -0.1394   0.8390   0.0491
   0.750   0.6742   0.00777   0.00178  -0.1387   0.8247   0.0599
   1.000   0.6991   0.00756   0.00179  -0.1379   0.8071   0.1520
   1.250   0.7238   0.00746   0.00177  -0.1370   0.7864   0.2045
   1.500   0.7456   0.00680   0.00192  -0.1359   0.7622   0.5676
   1.750   0.7757   0.00606   0.00193  -0.1362   0.7316   1.0000
   2.000   0.7982   0.00627   0.00192  -0.1348   0.6906   1.0000
   2.250   0.8201   0.00657   0.00199  -0.1333   0.6521   1.0000
   2.500   0.8423   0.00690   0.00213  -0.1320   0.6201   1.0000
   2.750   0.8645   0.00724   0.00229  -0.1307   0.5887   1.0000
   3.000   0.8867   0.00757   0.00246  -0.1294   0.5534   1.0000
   3.250   0.9079   0.00796   0.00264  -0.1280   0.5084   1.0000
   3.500   0.9189   0.00910   0.00303  -0.1248   0.3509   1.0000
   3.750   0.9196   0.01164   0.00414  -0.1204   0.0789   1.0000
   4.000   0.9416   0.01218   0.00457  -0.1193   0.0589   1.0000
   4.250   0.9645   0.01261   0.00497  -0.1182   0.0533   1.0000
   4.500   0.9867   0.01311   0.00549  -0.1171   0.0494   1.0000
   4.750   1.0099   0.01348   0.00589  -0.1161   0.0478   1.0000
   5.000   1.0325   0.01390   0.00635  -0.1151   0.0460   1.0000
   5.250   1.0544   0.01437   0.00684  -0.1139   0.0440   1.0000
   5.500   1.0753   0.01492   0.00739  -0.1126   0.0420   1.0000
   5.750   1.0929   0.01578   0.00830  -0.1107   0.0400   1.0000
   6.000   1.1098   0.01674   0.00932  -0.1087   0.0387   1.0000
   6.250   1.1318   0.01715   0.00976  -0.1076   0.0376   1.0000
   6.500   1.1526   0.01769   0.01033  -0.1064   0.0362   1.0000
   6.750   1.1726   0.01832   0.01101  -0.1049   0.0348   1.0000
   7.000   1.1924   0.01895   0.01167  -0.1036   0.0333   1.0000
   7.250   1.2111   0.01975   0.01245  -0.1021   0.0317   1.0000
   7.500   1.2283   0.02166   0.01440  -0.1005   0.0300   1.0000
   7.750   1.2494   0.02209   0.01490  -0.0993   0.0290   1.0000
   8.000   1.2702   0.02281   0.01571  -0.0981   0.0278   1.0000
   8.250   1.2901   0.02342   0.01637  -0.0968   0.0265   1.0000
   8.500   1.3089   0.02399   0.01696  -0.0955   0.0252   1.0000
   8.750   1.3280   0.02503   0.01799  -0.0943   0.0241   1.0000
   9.000   1.3512   0.02714   0.02025  -0.0939   0.0229   1.0000
   9.250   1.3701   0.02798   0.02122  -0.0924   0.0221   1.0000
   9.500   1.3888   0.02904   0.02241  -0.0911   0.0210   1.0000
   9.750   1.4053   0.02979   0.02323  -0.0894   0.0201   1.0000
  10.000   1.4180   0.03034   0.02384  -0.0871   0.0194   1.0000
  10.250   1.4294   0.03096   0.02450  -0.0847   0.0188   1.0000
  10.500   1.4492   0.03409   0.02782  -0.0844   0.0179   1.0000
  10.750   1.4587   0.03532   0.02928  -0.0816   0.0175   1.0000
  11.000   1.4682   0.03737   0.03159  -0.0791   0.0169   1.0000
  11.250   1.4743   0.03972   0.03421  -0.0762   0.0163   1.0000
  11.500   1.4772   0.04193   0.03664  -0.0731   0.0158   1.0000
  11.750   1.4784   0.04377   0.03866  -0.0700   0.0155   1.0000
  12.000   1.4804   0.04494   0.03993  -0.0672   0.0152   1.0000
  12.250   1.4813   0.04626   0.04135  -0.0645   0.0149   1.0000
  12.500   1.4850   0.04689   0.04199  -0.0623   0.0146   1.0000
  12.750   1.4828   0.04897   0.04420  -0.0600   0.0144   1.0000
  13.000   1.4746   0.05212   0.04751  -0.0577   0.0141   1.0000
  13.250   1.4471   0.05822   0.05398  -0.0551   0.0139   1.0000
  13.500   1.4301   0.06254   0.05855  -0.0536   0.0138   1.0000
  13.750   1.4097   0.06769   0.06398  -0.0529   0.0137   1.0000
  14.000   1.3863   0.07370   0.07025  -0.0532   0.0137   1.0000
  14.250   1.3607   0.08056   0.07735  -0.0547   0.0137   1.0000
  14.500   1.3340   0.08825   0.08525  -0.0575   0.0137   1.0000
  14.750   1.3076   0.09668   0.09387  -0.0615   0.0138   1.0000
  15.000   1.2805   0.10606   0.10343  -0.0668   0.0138   1.0000
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