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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 50,000
Max Cl/Cd: 46.45 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe427-il-50000-n5.txt
Download as CSV file: xf-goe427-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 427 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3283   0.11291   0.10608  -0.0279   1.0000   0.0550
  -8.250  -0.3335   0.11213   0.10542  -0.0276   1.0000   0.0554
  -8.000  -0.3391   0.11131   0.10472  -0.0272   1.0000   0.0556
  -7.750  -0.3407   0.11020   0.10371  -0.0282   1.0000   0.0559
  -7.500  -0.3400   0.10886   0.10247  -0.0298   1.0000   0.0560
  -7.250  -0.3343   0.10275   0.09643  -0.0264   1.0000   0.0570
  -7.000  -0.3297   0.09855   0.09226  -0.0240   1.0000   0.0586
  -6.750  -0.3276   0.09589   0.08967  -0.0231   1.0000   0.0603
  -6.500  -0.3260   0.09354   0.08739  -0.0227   1.0000   0.0627
  -6.250  -0.3237   0.09140   0.08532  -0.0230   1.0000   0.0653
  -6.000  -0.3187   0.08987   0.08384  -0.0256   1.0000   0.0686
  -5.750  -0.3061   0.08899   0.08296  -0.0315   1.0000   0.0699
  -5.500  -0.3054   0.08460   0.07867  -0.0284   1.0000   0.0715
  -5.250  -0.3023   0.08144   0.07557  -0.0262   1.0000   0.0748
  -5.000  -0.2919   0.07898   0.07311  -0.0278   1.0000   0.0799
  -4.750  -0.2636   0.07730   0.07130  -0.0367   1.0000   0.0838
  -4.500  -0.2638   0.07322   0.06730  -0.0328   1.0000   0.0859
  -4.250  -0.2525   0.07028   0.06437  -0.0330   1.0000   0.0901
  -4.000  -0.2134   0.06832   0.06219  -0.0425   1.0000   0.0971
  -3.750  -0.2093   0.06435   0.05831  -0.0399   1.0000   0.0995
  -3.500  -0.1871   0.06122   0.05511  -0.0421   0.9987   0.1056
  -3.250  -0.1419   0.05719   0.05092  -0.0496   0.9920   0.1168
  -2.750  -0.0301   0.04748   0.04038  -0.0666   0.9808   0.0670
  -2.500   0.0303   0.04275   0.03495  -0.0745   0.9764   0.0559
  -2.250   0.0637   0.03980   0.03191  -0.0776   0.9703   0.0603
  -2.000   0.1078   0.03687   0.02854  -0.0819   0.9649   0.0639
  -1.750   0.1512   0.03388   0.02498  -0.0854   0.9591   0.0640
  -1.500   0.1959   0.03154   0.02198  -0.0890   0.9543   0.0727
  -1.250   0.2320   0.02974   0.01972  -0.0907   0.9466   0.0765
  -1.000   0.2744   0.02799   0.01735  -0.0932   0.9412   0.0797
  -0.750   0.3089   0.02680   0.01564  -0.0943   0.9328   0.0849
  -0.500   0.3482   0.02619   0.01472  -0.0965   0.9257   0.1008
  -0.250   0.3840   0.02545   0.01363  -0.0978   0.9170   0.1068
   0.000   0.4193   0.02482   0.01279  -0.0990   0.9081   0.1152
   0.250   0.4581   0.02421   0.01208  -0.1009   0.9003   0.1333
   0.500   0.4906   0.02368   0.01170  -0.1019   0.8895   0.1807
   0.750   0.5253   0.02171   0.01143  -0.1035   0.8799   1.0000
   1.000   0.5617   0.02177   0.01110  -0.1048   0.8694   1.0000
   1.250   0.5991   0.02177   0.01086  -0.1063   0.8589   1.0000
   1.500   0.6315   0.02180   0.01075  -0.1068   0.8462   1.0000
   1.750   0.6637   0.02180   0.01067  -0.1073   0.8332   1.0000
   2.000   0.6957   0.02180   0.01061  -0.1077   0.8198   1.0000
   2.250   0.7274   0.02180   0.01057  -0.1080   0.8061   1.0000
   2.500   0.7585   0.02181   0.01062  -0.1082   0.7922   1.0000
   2.750   0.7893   0.02184   0.01068  -0.1083   0.7780   1.0000
   3.000   0.8196   0.02191   0.01079  -0.1083   0.7637   1.0000
   3.250   0.8494   0.02200   0.01096  -0.1082   0.7491   1.0000
   3.500   0.8788   0.02212   0.01122  -0.1081   0.7342   1.0000
   3.750   0.9076   0.02228   0.01150  -0.1079   0.7192   1.0000
   4.000   0.9361   0.02246   0.01182  -0.1076   0.7040   1.0000
   4.250   0.9640   0.02269   0.01227  -0.1072   0.6888   1.0000
   4.500   0.9897   0.02302   0.01279  -0.1065   0.6725   1.0000
   4.750   1.0151   0.02339   0.01337  -0.1058   0.6563   1.0000
   5.000   1.0405   0.02344   0.01359  -0.1045   0.6330   1.0000
   5.250   1.0607   0.02332   0.01358  -0.1017   0.5950   1.0000
   5.500   1.0825   0.02337   0.01364  -0.0994   0.5581   1.0000
   5.750   1.1028   0.02374   0.01412  -0.0973   0.5247   1.0000
   6.000   1.1177   0.02421   0.01456  -0.0943   0.4755   1.0000
   6.250   1.1272   0.02488   0.01520  -0.0906   0.4096   1.0000
   6.500   1.1334   0.02601   0.01594  -0.0867   0.3095   1.0000
   6.750   1.1304   0.02877   0.01765  -0.0826   0.1526   1.0000
   7.000   1.1327   0.03174   0.02001  -0.0797   0.0943   1.0000
   7.250   1.1385   0.03407   0.02228  -0.0769   0.0768   1.0000
   7.500   1.1441   0.03621   0.02450  -0.0741   0.0645   1.0000
   7.750   1.1507   0.03819   0.02668  -0.0713   0.0561   1.0000
   8.000   1.1570   0.04039   0.02901  -0.0685   0.0501   1.0000
   8.250   1.1664   0.04254   0.03128  -0.0663   0.0445   1.0000
   8.500   1.1889   0.04527   0.03415  -0.0649   0.0405   1.0000
   8.750   1.2164   0.04810   0.03720  -0.0646   0.0352   1.0000
   9.000   1.2543   0.05264   0.04212  -0.0655   0.0327   1.0000
   9.250   1.2696   0.05614   0.04622  -0.0637   0.0314   1.0000
   9.500   1.2766   0.05967   0.05027  -0.0615   0.0298   1.0000
   9.750   1.2780   0.06320   0.05424  -0.0590   0.0285   1.0000
  10.000   1.2744   0.06667   0.05808  -0.0562   0.0277   1.0000
  10.250   1.2668   0.07027   0.06202  -0.0534   0.0274   1.0000
  10.500   1.2556   0.07402   0.06609  -0.0510   0.0273   1.0000
  10.750   1.2416   0.07800   0.07038  -0.0492   0.0273   1.0000
  11.000   1.2254   0.08234   0.07500  -0.0481   0.0274   1.0000
  11.250   1.2076   0.08710   0.08002  -0.0481   0.0275   1.0000
  11.500   1.1889   0.09237   0.08552  -0.0491   0.0277   1.0000
  11.750   1.1695   0.09826   0.09162  -0.0512   0.0280   1.0000
  12.000   1.1498   0.10483   0.09836  -0.0544   0.0282   1.0000
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