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GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 802 AIRFOIL (goe802-il)
Reynolds number: 50,000
Max Cl/Cd: 38.73 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe802-il-50000-n5.txt
Download as CSV file: xf-goe802-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3003   0.11031   0.10414  -0.0218   1.0000   0.0979
  -7.250  -0.3114   0.10922   0.10316  -0.0193   1.0000   0.0995
  -7.000  -0.3166   0.10766   0.10167  -0.0188   0.9984   0.1017
  -6.750  -0.2967   0.10534   0.09933  -0.0306   0.9867   0.1066
  -6.500  -0.2760   0.10145   0.09542  -0.0385   0.9778   0.1083
  -6.250  -0.2567   0.09634   0.09032  -0.0357   0.9742   0.1122
  -6.000  -0.2365   0.09308   0.08704  -0.0397   0.9659   0.1189
  -5.750  -0.2092   0.09023   0.08410  -0.0525   0.9550   0.1250
  -5.500  -0.1924   0.08592   0.07982  -0.0504   0.9491   0.1286
  -5.250  -0.1671   0.08260   0.07644  -0.0549   0.9419   0.1356
  -5.000  -0.1388   0.07937   0.07311  -0.0637   0.9318   0.1426
  -4.750  -0.1176   0.07581   0.06956  -0.0640   0.9255   0.1478
  -4.500  -0.0860   0.07294   0.06656  -0.0723   0.9156   0.1593
  -4.250  -0.0627   0.06963   0.06325  -0.0727   0.9094   0.1684
  -4.000  -0.0387   0.06675   0.06032  -0.0759   0.8999   0.1806
  -3.750  -0.0042   0.06359   0.05707  -0.0809   0.8938   0.1967
  -3.500   0.0203   0.06111   0.05453  -0.0836   0.8836   0.2120
  -3.250   0.0571   0.05798   0.05131  -0.0877   0.8786   0.2304
  -2.750   0.1801   0.04793   0.03981  -0.1079   0.8633   0.0900
  -2.500   0.2062   0.04580   0.03753  -0.1089   0.8525   0.0883
  -2.250   0.2489   0.04303   0.03445  -0.1126   0.8471   0.0851
  -2.000   0.2801   0.04088   0.03189  -0.1139   0.8361   0.0806
  -1.500   0.3523   0.03723   0.02740  -0.1170   0.8190   0.0758
  -1.250   0.3881   0.03558   0.02544  -0.1183   0.8112   0.0749
  -1.000   0.4201   0.03431   0.02387  -0.1188   0.8012   0.0751
  -0.750   0.4504   0.03331   0.02255  -0.1189   0.7907   0.0763
  -0.500   0.4869   0.03214   0.02102  -0.1196   0.7829   0.0773
  -0.250   0.5135   0.03141   0.02010  -0.1191   0.7708   0.0775
   0.000   0.5446   0.03043   0.01894  -0.1190   0.7614   0.0780
   0.250   0.5761   0.02961   0.01793  -0.1189   0.7514   0.0790
   0.500   0.6033   0.02910   0.01729  -0.1182   0.7396   0.0804
   0.750   0.6353   0.02842   0.01648  -0.1182   0.7307   0.0839
   1.000   0.6629   0.02805   0.01600  -0.1176   0.7194   0.0886
   1.250   0.6892   0.02780   0.01565  -0.1169   0.7076   0.0927
   1.500   0.7198   0.02731   0.01511  -0.1168   0.6981   0.0981
   1.750   0.7476   0.02709   0.01482  -0.1163   0.6870   0.1060
   2.000   0.7740   0.02693   0.01475  -0.1158   0.6752   0.1252
   2.250   0.7998   0.02491   0.01455  -0.1150   0.6658   1.0000
   2.500   0.8268   0.02509   0.01439  -0.1142   0.6546   1.0000
   2.750   0.8517   0.02542   0.01450  -0.1134   0.6428   1.0000
   3.000   0.8794   0.02558   0.01445  -0.1130   0.6326   1.0000
   3.250   0.9067   0.02577   0.01447  -0.1125   0.6219   1.0000
   3.500   0.9305   0.02619   0.01479  -0.1117   0.6102   1.0000
   3.750   0.9575   0.02645   0.01492  -0.1113   0.6002   1.0000
   4.000   0.9840   0.02674   0.01511  -0.1108   0.5898   1.0000
   4.250   1.0072   0.02725   0.01557  -0.1100   0.5785   1.0000
   4.500   1.0350   0.02752   0.01575  -0.1097   0.5694   1.0000
   4.750   1.0583   0.02804   0.01626  -0.1090   0.5586   1.0000
   5.000   1.0818   0.02859   0.01678  -0.1083   0.5484   1.0000
   5.250   1.1095   0.02890   0.01705  -0.1080   0.5397   1.0000
   5.500   1.1297   0.02966   0.01785  -0.1070   0.5290   1.0000
   5.750   1.1565   0.03004   0.01819  -0.1066   0.5203   1.0000
   6.000   1.1773   0.03074   0.01895  -0.1056   0.5099   1.0000
   6.250   1.1985   0.03134   0.01959  -0.1046   0.4988   1.0000
   6.500   1.2240   0.03160   0.01980  -0.1039   0.4880   1.0000
   6.750   1.2429   0.03219   0.02045  -0.1025   0.4756   1.0000
   7.000   1.2604   0.03289   0.02123  -0.1010   0.4635   1.0000
   7.250   1.2816   0.03339   0.02176  -0.0999   0.4529   1.0000
   7.500   1.3026   0.03392   0.02233  -0.0988   0.4424   1.0000
   7.750   1.3175   0.03482   0.02336  -0.0971   0.4315   1.0000
   8.000   1.3379   0.03537   0.02398  -0.0960   0.4215   1.0000
   8.250   1.3553   0.03605   0.02474  -0.0945   0.4108   1.0000
   8.500   1.3680   0.03703   0.02586  -0.0926   0.4000   1.0000
   8.750   1.3866   0.03764   0.02655  -0.0913   0.3899   1.0000
   9.000   1.4008   0.03845   0.02746  -0.0895   0.3790   1.0000
   9.250   1.4097   0.03959   0.02875  -0.0872   0.3679   1.0000
   9.500   1.4245   0.04035   0.02958  -0.0855   0.3574   1.0000
   9.750   1.4349   0.04126   0.03057  -0.0832   0.3466   1.0000
  10.000   1.4370   0.04273   0.03222  -0.0804   0.3356   1.0000
  10.250   1.4470   0.04377   0.03332  -0.0783   0.3250   1.0000
  10.500   1.4557   0.04491   0.03454  -0.0762   0.3143   1.0000
  10.750   1.4530   0.04691   0.03671  -0.0735   0.3033   1.0000
  11.000   1.4567   0.04844   0.03831  -0.0713   0.2924   1.0000
  11.250   1.4637   0.04965   0.03956  -0.0694   0.2814   1.0000
  11.500   1.4532   0.05259   0.04270  -0.0671   0.2708   1.0000
  11.750   1.4513   0.05486   0.04505  -0.0654   0.2608   1.0000
  12.000   1.4562   0.05644   0.04664  -0.0639   0.2510   1.0000
  12.250   1.4432   0.06023   0.05065  -0.0626   0.2417   1.0000
  12.500   1.4452   0.06241   0.05286  -0.0614   0.2335   1.0000
  12.750   1.4379   0.06590   0.05652  -0.0606   0.2255   1.0000
  13.000   1.4385   0.06850   0.05919  -0.0597   0.2185   1.0000
  13.250   1.4295   0.07251   0.06340  -0.0594   0.2117   1.0000
  13.500   1.4381   0.07417   0.06508  -0.0585   0.2057   1.0000
  13.750   1.4175   0.08012   0.07129  -0.0590   0.1999   1.0000
  14.000   1.4259   0.08184   0.07306  -0.0582   0.1943   1.0000
  14.250   1.4114   0.08720   0.07859  -0.0589   0.1893   1.0000
  14.500   1.3866   0.09447   0.08606  -0.0606   0.1841   1.0000
  14.750   1.4150   0.09282   0.08439  -0.0585   0.1788   1.0000
  15.000   1.3592   0.10605   0.09790  -0.0634   0.1746   1.0000
  15.250   1.2997   0.12142   0.11341  -0.0702   0.1683   1.0000
  15.500   1.3414   0.11641   0.10847  -0.0663   0.1651   1.0000
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