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GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 100,000
Max Cl/Cd: 51.65 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe478-il-100000.txt
Download as CSV file: xf-goe478-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3649   0.11425   0.10956  -0.0242   1.0000   0.1213
  -8.250  -0.4098   0.11480   0.11022  -0.0243   1.0000   0.1224
  -8.000  -0.4521   0.11445   0.10996  -0.0257   0.9982   0.1227
  -7.750  -0.3896   0.10744   0.10290  -0.0222   0.9982   0.1248
  -7.500  -0.3595   0.10389   0.09933  -0.0242   0.9942   0.1284
  -7.250  -0.3502   0.10078   0.09622  -0.0283   0.9883   0.1333
  -7.000  -0.3989   0.09741   0.09281  -0.0446   0.9735   0.1374
  -6.750  -0.3539   0.09334   0.08881  -0.0391   0.9723   0.1393
  -6.500  -0.3250   0.09022   0.08568  -0.0398   0.9676   0.1428
  -6.250  -0.3177   0.08716   0.08261  -0.0428   0.9600   0.1471
  -6.000  -0.3374   0.08219   0.07753  -0.0529   0.9493   0.1535
  -5.750  -0.3118   0.07932   0.07472  -0.0512   0.9454   0.1556
  -5.500  -0.2832   0.07626   0.07163  -0.0538   0.9414   0.1604
  -5.250  -0.2968   0.07249   0.06762  -0.0594   0.9303   0.1697
  -5.000  -0.2664   0.06933   0.06456  -0.0596   0.9267   0.1724
  -4.750  -0.2570   0.06740   0.06264  -0.0582   0.9189   0.1769
  -4.500  -0.2386   0.06360   0.05865  -0.0629   0.9118   0.1886
  -4.250  -0.2139   0.06138   0.05644  -0.0635   0.9062   0.1956
  -4.000  -0.2075   0.04448   0.03745  -0.0714   0.8976   0.1099
  -3.750  -0.1703   0.04152   0.03435  -0.0738   0.8929   0.1070
  -3.500  -0.1521   0.03920   0.03173  -0.0727   0.8846   0.1051
  -3.250  -0.1208   0.03683   0.02892  -0.0736   0.8778   0.1052
  -3.000  -0.0768   0.03464   0.02621  -0.0762   0.8737   0.1073
  -2.750  -0.0615   0.03358   0.02484  -0.0739   0.8626   0.1082
  -2.500  -0.0187   0.03179   0.02274  -0.0761   0.8575   0.1106
  -2.250   0.0061   0.03103   0.02196  -0.0755   0.8480   0.1139
  -2.000   0.0446   0.03011   0.02088  -0.0769   0.8410   0.1211
  -1.750   0.0953   0.02870   0.01948  -0.0803   0.8374   0.1300
  -1.500   0.1129   0.02830   0.01899  -0.0781   0.8246   0.1382
  -1.250   0.1616   0.02720   0.01807  -0.0811   0.8206   0.1580
  -1.000   0.1829   0.02692   0.01787  -0.0796   0.8087   0.1795
  -0.750   0.2291   0.02579   0.01691  -0.0821   0.8039   0.2268
  -0.500   0.2810   0.02447   0.01586  -0.0856   0.8010   0.2809
  -0.250   0.2974   0.02414   0.01579  -0.0833   0.7875   0.3231
   0.000   0.3380   0.02196   0.01519  -0.0845   0.7840   0.6467
   0.500   0.5153   0.02072   0.01398  -0.1056   0.7719   1.0000
   0.750   0.5579   0.02026   0.01333  -0.1074   0.7653   1.0000
   1.000   0.5736   0.02052   0.01349  -0.1049   0.7521   1.0000
   1.250   0.6160   0.02010   0.01290  -0.1066   0.7459   1.0000
   1.500   0.6291   0.02045   0.01318  -0.1037   0.7322   1.0000
   1.750   0.6715   0.02006   0.01263  -0.1055   0.7264   1.0000
   2.000   0.6807   0.02058   0.01311  -0.1021   0.7127   1.0000
   2.250   0.7122   0.02052   0.01294  -0.1021   0.7048   1.0000
   2.500   0.7297   0.02081   0.01319  -0.1000   0.6936   1.0000
   2.750   0.7561   0.02092   0.01322  -0.0994   0.6852   1.0000
   3.000   0.7761   0.02117   0.01342  -0.0977   0.6752   1.0000
   3.250   0.8018   0.02128   0.01348  -0.0969   0.6669   1.0000
   3.500   0.8221   0.02152   0.01368  -0.0953   0.6573   1.0000
   3.750   0.8477   0.02160   0.01371  -0.0945   0.6490   1.0000
   4.000   0.8709   0.02164   0.01372  -0.0933   0.6393   1.0000
   4.250   0.8926   0.02175   0.01380  -0.0917   0.6295   1.0000
   4.500   0.9237   0.02149   0.01348  -0.0916   0.6206   1.0000
   4.750   0.9410   0.02176   0.01375  -0.0895   0.6101   1.0000
   5.000   0.9776   0.02138   0.01326  -0.0903   0.6021   1.0000
   5.250   0.9920   0.02177   0.01369  -0.0877   0.5911   1.0000
   5.500   1.0228   0.02164   0.01348  -0.0877   0.5820   1.0000
   5.750   1.0457   0.02176   0.01359  -0.0865   0.5714   1.0000
   6.000   1.0682   0.02198   0.01381  -0.0852   0.5608   1.0000
   6.250   1.1046   0.02185   0.01352  -0.0861   0.5506   1.0000
   6.500   1.1182   0.02233   0.01407  -0.0835   0.5386   1.0000
   6.750   1.1423   0.02262   0.01434  -0.0825   0.5272   1.0000
   7.000   1.1752   0.02277   0.01435  -0.0830   0.5155   1.0000
   7.250   1.1872   0.02330   0.01497  -0.0801   0.5026   1.0000
   7.500   1.2073   0.02372   0.01540  -0.0785   0.4899   1.0000
   7.750   1.2322   0.02401   0.01560  -0.0777   0.4764   1.0000
   8.000   1.2525   0.02425   0.01579  -0.0761   0.4614   1.0000
   8.250   1.2627   0.02457   0.01615  -0.0728   0.4457   1.0000
   8.500   1.2735   0.02484   0.01646  -0.0696   0.4297   1.0000
   8.750   1.2834   0.02509   0.01671  -0.0662   0.4135   1.0000
   9.000   1.2919   0.02537   0.01700  -0.0627   0.3973   1.0000
   9.250   1.2985   0.02571   0.01733  -0.0590   0.3809   1.0000
   9.500   1.3016   0.02609   0.01770  -0.0547   0.3646   1.0000
   9.750   1.3029   0.02657   0.01815  -0.0503   0.3480   1.0000
  10.000   1.3039   0.02719   0.01872  -0.0461   0.3309   1.0000
  10.250   1.3055   0.02794   0.01942  -0.0423   0.3139   1.0000
  10.500   1.3070   0.02885   0.02025  -0.0387   0.2969   1.0000
  10.750   1.3094   0.02989   0.02120  -0.0355   0.2807   1.0000
  11.000   1.3125   0.03107   0.02229  -0.0326   0.2651   1.0000
  11.250   1.3165   0.03235   0.02347  -0.0300   0.2503   1.0000
  11.500   1.3221   0.03370   0.02471  -0.0277   0.2364   1.0000
  11.750   1.3294   0.03508   0.02596  -0.0257   0.2233   1.0000
  12.000   1.3398   0.03645   0.02715  -0.0240   0.2104   1.0000
  12.250   1.3413   0.03809   0.02891  -0.0217   0.1995   1.0000
  12.500   1.3497   0.03968   0.03046  -0.0201   0.1891   1.0000
  12.750   1.3678   0.04099   0.03158  -0.0193   0.1791   1.0000
  13.000   1.3696   0.04280   0.03357  -0.0173   0.1716   1.0000
  13.250   1.3896   0.04414   0.03476  -0.0167   0.1637   1.0000
  13.500   1.3916   0.04604   0.03686  -0.0149   0.1578   1.0000
  13.750   1.4252   0.04709   0.03763  -0.0154   0.1507   1.0000
  14.000   1.4211   0.04929   0.04014  -0.0132   0.1472   1.0000
  14.250   1.4260   0.05123   0.04224  -0.0119   0.1430   1.0000
  14.500   1.4560   0.05231   0.04314  -0.0121   0.1379   1.0000
  14.750   1.4577   0.05472   0.04576  -0.0106   0.1351   1.0000
  15.000   1.4528   0.05733   0.04865  -0.0090   0.1326   1.0000
  15.250   1.4512   0.05988   0.05139  -0.0077   0.1301   1.0000
  15.500   1.4581   0.06195   0.05354  -0.0069   0.1273   1.0000
  15.750   1.4873   0.06354   0.05503  -0.0071   0.1236   1.0000
  16.000   1.4663   0.06723   0.05905  -0.0054   0.1226   1.0000
  16.250   1.4445   0.07143   0.06356  -0.0044   0.1215   1.0000
  16.500   1.4200   0.07620   0.06863  -0.0039   0.1205   1.0000
  16.750   1.3914   0.08175   0.07447  -0.0041   0.1198   1.0000
  17.000   1.3529   0.08889   0.08192  -0.0054   0.1195   1.0000
  17.250   1.2897   0.10023   0.09362  -0.0094   0.1202   1.0000
  17.500   1.1301   0.13193   0.12574  -0.0261   0.1238   1.0000
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