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GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 435 AIRFOIL (goe435-il)
Reynolds number: 100,000
Max Cl/Cd: 25.13 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe435-il-100000.txt
Download as CSV file: xf-goe435-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 435 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250   0.0111   0.12237   0.11639  -0.0942   0.9329   0.1752
 -12.000   0.0119   0.11853   0.11253  -0.0959   0.9243   0.1774
 -11.750  -0.0255   0.10989   0.10383  -0.1005   0.9191   0.1849
 -11.500   0.0176   0.11135   0.10531  -0.0991   0.9106   0.1887
 -11.000   0.0118   0.10587   0.09978  -0.1006   0.8953   0.2164
 -10.750   0.0287   0.10625   0.10018  -0.0996   0.8864   0.2320
 -10.500   0.0986   0.11129   0.10529  -0.0947   0.8746   0.2525
 -10.250   0.1829   0.10982   0.10403  -0.0961   0.8397   0.2736
 -10.000   0.0866   0.10950   0.10343  -0.0940   0.8586   0.2951
  -9.750   0.1353   0.10703   0.10090  -0.0919   0.8499   0.3027
  -9.500   0.1220   0.10589   0.09968  -0.0920   0.8437   0.3124
  -9.250   0.1559   0.10396   0.09774  -0.0914   0.8334   0.3176
  -9.000   0.1052   0.10591   0.09964  -0.0919   0.8262   0.3276
  -8.750   0.1610   0.10132   0.09496  -0.0905   0.8195   0.3301
  -8.500   0.1891   0.09968   0.09333  -0.0904   0.8090   0.3347
  -8.250   0.1934   0.09890   0.09250  -0.0900   0.8012   0.3418
  -6.250  -0.1314   0.04196   0.03433  -0.1196   0.7438   0.2748
  -6.000  -0.1512   0.04124   0.03346  -0.1175   0.7298   0.2754
  -5.750  -0.1325   0.03946   0.03136  -0.1189   0.7245   0.2773
  -5.500  -0.1028   0.03845   0.03023  -0.1199   0.7208   0.2796
  -5.250  -0.0664   0.03836   0.03023  -0.1201   0.7178   0.2823
  -5.000  -0.0837   0.03975   0.03168  -0.1160   0.7040   0.2830
  -4.750  -0.0583   0.03953   0.03143  -0.1161   0.6994   0.2854
  -4.500  -0.0264   0.03877   0.03057  -0.1172   0.6962   0.2879
  -4.250   0.0074   0.03783   0.02946  -0.1187   0.6934   0.2904
  -4.000  -0.0183   0.04007   0.03173  -0.1141   0.6808   0.2908
  -3.750  -0.0010   0.04011   0.03165  -0.1139   0.6751   0.2925
  -3.500   0.0330   0.03939   0.03077  -0.1153   0.6721   0.2946
  -3.250   0.0724   0.03871   0.03014  -0.1163   0.6700   0.2968
  -3.000   0.0225   0.04268   0.03418  -0.1098   0.6562   0.2967
  -2.750   0.0377   0.04328   0.03483  -0.1089   0.6504   0.2985
  -2.500   0.0837   0.04232   0.03388  -0.1105   0.6481   0.3020
  -2.250   0.1385   0.04080   0.03228  -0.1131   0.6465   0.3069
  -2.000   0.0886   0.04504   0.03657  -0.1071   0.6315   0.3067
  -1.750   0.1254   0.04437   0.03583  -0.1081   0.6273   0.3114
  -1.500   0.1724   0.04323   0.03480  -0.1092   0.6252   0.3163
  -1.250   0.2301   0.04155   0.03309  -0.1116   0.6241   0.3253
  -1.000   0.1770   0.04695   0.03857  -0.1066   0.6084   0.3245
  -0.750   0.2158   0.04627   0.03796  -0.1071   0.6051   0.3325
  -0.500   0.2642   0.04490   0.03659  -0.1083   0.6033   0.3465
  -0.250   0.2365   0.04929   0.04108  -0.1056   0.5896   0.3486
   0.000   0.2728   0.04891   0.04073  -0.1060   0.5855   0.3659
   0.250   0.3171   0.04789   0.03979  -0.1062   0.5833   0.3879
   0.500   0.3642   0.04654   0.03850  -0.1062   0.5821   0.4118
   0.750   0.4152   0.04489   0.03685  -0.1064   0.5814   0.4343
   1.000   0.4704   0.04344   0.03537  -0.1076   0.5806   0.4543
   1.250   0.3565   0.05424   0.04641  -0.1009   0.5498   0.4405
   1.500   0.3896   0.05403   0.04611  -0.1008   0.5450   0.4571
   1.750   0.4272   0.05294   0.04517  -0.0994   0.5428   0.4688
   2.000   0.4761   0.05121   0.04332  -0.1000   0.5417   0.4837
   2.250   0.5203   0.04924   0.04146  -0.0988   0.5411   0.4935
   2.500   0.5739   0.04697   0.03908  -0.0996   0.5405   0.5058
   2.750   0.6279   0.04465   0.03677  -0.1000   0.5399   0.5157
   3.000   0.6930   0.04242   0.03448  -0.1022   0.5393   0.5280
   3.250   0.6295   0.04845   0.04067  -0.0961   0.5197   0.5273
   3.500   0.6905   0.04572   0.03781  -0.0978   0.5193   0.5375
   3.750   0.7507   0.04313   0.03523  -0.0987   0.5187   0.5472
   4.000   0.8356   0.04045   0.03235  -0.1043   0.5178   0.5584
   4.250   0.7064   0.05051   0.04274  -0.0929   0.4919   0.5525
   4.500   0.7758   0.04719   0.03924  -0.0954   0.4921   0.5620
   4.750   0.8539   0.04322   0.03524  -0.0974   0.4930   0.5717
   5.000   0.5951   0.07028   0.06271  -0.0889   0.4388   0.5546
   5.250   0.6340   0.06921   0.06151  -0.0894   0.4363   0.5617
   5.500   0.6725   0.06729   0.05968  -0.0883   0.4350   0.5689
   5.750   0.7167   0.06495   0.05733  -0.0877   0.4343   0.5776
   6.000   0.7669   0.06227   0.05454  -0.0881   0.4338   0.5854
   6.250   0.8194   0.05921   0.05144  -0.0882   0.4335   0.5923
   6.500   0.8752   0.05595   0.04818  -0.0882   0.4333   0.6012
   6.750   0.9457   0.05211   0.04419  -0.0898   0.4332   0.6132
   7.000   1.0184   0.04818   0.04022  -0.0912   0.4327   0.6241
   7.250   1.1096   0.04416   0.03597  -0.0955   0.4314   0.6376
   7.500   0.9577   0.05788   0.05014  -0.0865   0.4130   0.6290
   7.750   1.0350   0.05340   0.04550  -0.0884   0.4129   0.6418
   8.000   1.1171   0.04892   0.04092  -0.0906   0.4123   0.6517
   9.250   0.5409   0.14161   0.13470  -0.0991   0.3645   0.6108
   9.500   0.6129   0.13370   0.12674  -0.0949   0.3380   0.6259
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