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GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 427 AIRFOIL (goe427-il)
Reynolds number: 50,000
Max Cl/Cd: 45.83 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe427-il-50000.txt
Download as CSV file: xf-goe427-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3483   0.10326   0.09657  -0.0224   1.0000   0.1076
  -7.500  -0.3531   0.10237   0.09580  -0.0227   1.0000   0.1099
  -7.250  -0.3567   0.10244   0.09598  -0.0257   1.0000   0.1112
  -7.000  -0.3496   0.09697   0.09058  -0.0229   1.0000   0.1139
  -6.750  -0.3447   0.09378   0.08744  -0.0216   1.0000   0.1181
  -6.500  -0.3425   0.09192   0.08565  -0.0225   1.0000   0.1224
  -6.250  -0.3372   0.09274   0.08650  -0.0299   1.0000   0.1252
  -6.000  -0.3346   0.08653   0.08039  -0.0233   1.0000   0.1290
  -5.750  -0.3289   0.08401   0.07792  -0.0236   1.0000   0.1354
  -5.500  -0.3184   0.08239   0.07631  -0.0283   1.0000   0.1400
  -5.250  -0.3152   0.07845   0.07244  -0.0245   1.0000   0.1455
  -5.000  -0.3004   0.07650   0.07048  -0.0294   1.0000   0.1542
  -4.750  -0.2950   0.07314   0.06717  -0.0269   1.0000   0.1636
  -4.500  -0.2849   0.07013   0.06414  -0.0274   1.0000   0.1730
  -4.250  -0.2717   0.06731   0.06132  -0.0288   1.0000   0.1856
  -4.000  -0.2575   0.06450   0.05850  -0.0299   1.0000   0.1993
  -3.750  -0.2428   0.06162   0.05561  -0.0307   1.0000   0.2143
  -3.500  -0.2194   0.05931   0.05319  -0.0345   1.0000   0.2375
  -3.250  -0.2089   0.05598   0.04990  -0.0331   1.0000   0.2544
  -3.000  -0.1923   0.05317   0.04708  -0.0336   1.0000   0.2819
  -2.750  -0.1784   0.05033   0.04425  -0.0328   1.0000   0.3135
  -2.000  -0.1622   0.04168   0.03584  -0.0219   1.0000   0.5017
  -1.750  -0.1554   0.03858   0.03286  -0.0177   1.0000   0.5502
  -1.500  -0.1388   0.03582   0.03012  -0.0162   1.0000   0.5938
  -1.250  -0.1090   0.03326   0.02749  -0.0184   1.0000   0.6221
  -1.000   0.0728   0.03420   0.02611  -0.0585   1.0000   0.2550
  -0.750   0.1203   0.03216   0.02306  -0.0617   1.0000   0.1824
  -0.500   0.1485   0.03067   0.02123  -0.0621   1.0000   0.1725
  -0.250   0.1738   0.02980   0.02002  -0.0622   1.0000   0.1774
   0.000   0.1987   0.02895   0.01885  -0.0622   1.0000   0.1751
   0.250   0.2224   0.02839   0.01798  -0.0621   1.0000   0.1753
   0.500   0.2472   0.02814   0.01733  -0.0622   1.0000   0.1791
   0.750   0.2700   0.02807   0.01709  -0.0622   1.0000   0.1916
   1.000   0.2918   0.02818   0.01708  -0.0623   1.0000   0.2117
   1.250   0.3349   0.02816   0.01704  -0.0659   0.9920   0.2502
   1.500   0.3912   0.02637   0.01643  -0.0714   0.9776   1.0000
   1.750   0.4436   0.02757   0.01720  -0.0772   0.9587   1.0000
   2.000   0.4919   0.02856   0.01799  -0.0820   0.9401   1.0000
   2.250   0.5338   0.02938   0.01870  -0.0856   0.9208   1.0000
   2.500   0.5788   0.03012   0.01938  -0.0895   0.9033   1.0000
   2.750   0.6218   0.03077   0.02005  -0.0928   0.8865   1.0000
   3.000   0.6542   0.03142   0.02075  -0.0942   0.8678   1.0000
   3.250   0.6922   0.03200   0.02139  -0.0964   0.8510   1.0000
   3.500   0.7319   0.03246   0.02197  -0.0986   0.8349   1.0000
   3.750   0.7724   0.03284   0.02256  -0.1008   0.8194   1.0000
   4.000   0.8143   0.03308   0.02300  -0.1029   0.8043   1.0000
   4.250   0.8380   0.03388   0.02397  -0.1025   0.7863   1.0000
   4.500   0.8714   0.03434   0.02466  -0.1032   0.7699   1.0000
   4.750   0.9402   0.03198   0.02279  -0.1054   0.7479   1.0000
   5.000   0.9873   0.02995   0.02110  -0.1041   0.7186   1.0000
   5.250   1.0250   0.02825   0.01977  -0.1016   0.6860   1.0000
   5.500   1.0624   0.02634   0.01812  -0.0985   0.6490   1.0000
   5.750   1.0803   0.02414   0.01581  -0.0912   0.5777   1.0000
   6.000   1.0894   0.02377   0.01529  -0.0848   0.4995   1.0000
   6.250   1.0788   0.02480   0.01544  -0.0763   0.3159   1.0000
   6.500   1.0728   0.02847   0.01749  -0.0714   0.1785   1.0000
   6.750   1.0835   0.03116   0.01983  -0.0687   0.1453   1.0000
   7.000   1.1030   0.03349   0.02212  -0.0670   0.1259   1.0000
   7.250   1.1360   0.03609   0.02469  -0.0666   0.1131   1.0000
   7.500   1.1687   0.03892   0.02757  -0.0665   0.1010   1.0000
   7.750   1.2076   0.04306   0.03181  -0.0672   0.0967   1.0000
   8.000   1.2311   0.04653   0.03588  -0.0657   0.0944   1.0000
   8.250   1.2476   0.04999   0.03988  -0.0637   0.0909   1.0000
   8.500   1.2615   0.05394   0.04435  -0.0616   0.0897   1.0000
   8.750   1.2699   0.05845   0.04953  -0.0591   0.0915   1.0000
   9.000   1.2746   0.06321   0.05479  -0.0567   0.0938   1.0000
   9.250   1.2800   0.06849   0.06039  -0.0548   0.0962   1.0000
   9.500   1.2726   0.07280   0.06527  -0.0518   0.0994   1.0000
   9.750   1.2463   0.07732   0.07034  -0.0485   0.1025   1.0000
  10.000   1.2237   0.08200   0.07531  -0.0462   0.1048   1.0000
  10.250   1.2031   0.08665   0.08012  -0.0444   0.1068   1.0000
  10.500   1.2005   0.09248   0.08608  -0.0441   0.1113   1.0000
  10.750   1.1646   0.09737   0.09111  -0.0446   0.1118   1.0000
  11.000   1.1264   0.10409   0.09784  -0.0483   0.1124   1.0000
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