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GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 770 AIRFOIL (goe770-il)
Reynolds number: 100,000
Max Cl/Cd: 19.17 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe770-il-100000.txt
Download as CSV file: xf-goe770-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 770 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5988   0.07697   0.07169  -0.0681   1.0000   0.1048
 -12.500  -0.6100   0.07166   0.06635  -0.0700   1.0000   0.1042
 -12.250  -0.6342   0.06633   0.06097  -0.0718   1.0000   0.1033
 -12.000  -0.6646   0.06210   0.05669  -0.0722   1.0000   0.1025
 -11.750  -0.6838   0.05734   0.05164  -0.0753   0.9663   0.1018
 -11.500  -0.6868   0.05256   0.04639  -0.0774   0.9333   0.1016
 -11.250  -0.6870   0.04922   0.04259  -0.0769   0.9058   0.1019
 -11.000  -0.6877   0.04670   0.03962  -0.0748   0.8832   0.1028
 -10.750  -0.6871   0.04460   0.03704  -0.0723   0.8651   0.1038
 -10.500  -0.6842   0.04285   0.03475  -0.0695   0.8503   0.1049
 -10.250  -0.6657   0.04053   0.03235  -0.0689   0.8360   0.1066
 -10.000  -0.6444   0.03895   0.03069  -0.0682   0.8241   0.1084
  -9.750  -0.6256   0.03753   0.02908  -0.0671   0.8132   0.1106
  -9.500  -0.6084   0.03626   0.02751  -0.0659   0.8037   0.1133
  -9.250  -0.5931   0.03522   0.02605  -0.0642   0.7942   0.1158
  -9.000  -0.5661   0.03350   0.02439  -0.0642   0.7864   0.1191
  -8.750  -0.5417   0.03242   0.02326  -0.0639   0.7771   0.1226
  -8.500  -0.5201   0.03152   0.02210  -0.0628   0.7697   0.1268
  -8.250  -0.4927   0.03026   0.02094  -0.0629   0.7630   0.1316
  -8.000  -0.4679   0.02943   0.02008  -0.0626   0.7554   0.1371
  -7.750  -0.4428   0.02844   0.01907  -0.0621   0.7490   0.1432
  -7.500  -0.4187   0.02770   0.01837  -0.0615   0.7431   0.1507
  -7.250  -0.3951   0.02691   0.01771  -0.0611   0.7359   0.1589
  -7.000  -0.3729   0.02629   0.01710  -0.0602   0.7300   0.1694
  -6.750  -0.3522   0.02565   0.01654  -0.0590   0.7250   0.1821
  -6.500  -0.3329   0.02515   0.01622  -0.0579   0.7191   0.1989
  -6.250  -0.3156   0.02463   0.01600  -0.0566   0.7127   0.2225
  -6.000  -0.2992   0.02404   0.01563  -0.0548   0.7074   0.2690
  -5.750  -0.2876   0.02317   0.01517  -0.0522   0.7032   0.3388
  -5.500  -0.2737   0.02300   0.01548  -0.0499   0.6975   0.4056
  -5.250  -0.2545   0.02332   0.01596  -0.0483   0.6912   0.4563
  -5.000  -0.2323   0.02365   0.01627  -0.0467   0.6859   0.4920
  -4.750  -0.2092   0.02396   0.01643  -0.0453   0.6816   0.5222
  -4.500  -0.1877   0.02449   0.01700  -0.0441   0.6754   0.5455
  -4.250  -0.1650   0.02490   0.01742  -0.0429   0.6690   0.5674
  -4.000  -0.1405   0.02520   0.01770  -0.0415   0.6639   0.5894
  -3.750  -0.1150   0.02549   0.01792  -0.0401   0.6596   0.6110
  -3.500  -0.0953   0.02610   0.01859  -0.0388   0.6528   0.6306
  -3.250  -0.0713   0.02653   0.01909  -0.0375   0.6465   0.6476
  -3.000  -0.0453   0.02671   0.01924  -0.0361   0.6417   0.6642
  -2.750  -0.0191   0.02690   0.01932  -0.0348   0.6378   0.6814
  -2.500  -0.0034   0.02759   0.02008  -0.0333   0.6302   0.6983
  -2.250   0.0204   0.02798   0.02052  -0.0318   0.6241   0.7128
  -2.000   0.0468   0.02803   0.02049  -0.0306   0.6197   0.7266
  -1.750   0.0730   0.02807   0.02037  -0.0298   0.6161   0.7400
  -1.500   0.0867   0.02895   0.02141  -0.0284   0.6073   0.7487
  -1.250   0.1100   0.02908   0.02148  -0.0276   0.6016   0.7600
  -1.000   0.1390   0.02893   0.02123  -0.0270   0.5976   0.7696
  -0.750   0.1624   0.02923   0.02148  -0.0261   0.5928   0.7798
  -0.500   0.1732   0.03015   0.02250  -0.0247   0.5839   0.7894
  -0.250   0.1998   0.03020   0.02250  -0.0241   0.5792   0.7986
   0.000   0.2295   0.02998   0.02215  -0.0237   0.5758   0.8102
   0.250   0.2395   0.03115   0.02344  -0.0218   0.5675   0.8208
   0.500   0.2572   0.03162   0.02392  -0.0207   0.5607   0.8329
   0.750   0.2884   0.03142   0.02365  -0.0203   0.5571   0.8440
   1.000   0.3218   0.03117   0.02328  -0.0204   0.5543   0.8552
   1.250   0.3113   0.03360   0.02596  -0.0175   0.5429   0.8701
   1.500   0.3431   0.03368   0.02600  -0.0177   0.5386   0.8818
   1.750   0.3826   0.03326   0.02548  -0.0185   0.5359   0.8959
   2.000   0.4288   0.03291   0.02501  -0.0204   0.5335   0.9089
   2.250   0.4177   0.03642   0.02881  -0.0193   0.5201   0.9292
   2.500   0.4756   0.03606   0.02835  -0.0236   0.5174   0.9383
   2.750   0.5316   0.03552   0.02768  -0.0276   0.5153   0.9492
   3.000   0.5313   0.04099   0.03344  -0.0316   0.5017   0.9688
   3.250   0.5951   0.04037   0.03273  -0.0370   0.4991   0.9782
   3.500   0.6656   0.03926   0.03150  -0.0430   0.4972   0.9846
   3.750   0.7330   0.03824   0.03035  -0.0489   0.4955   0.9927
   4.000   0.4995   0.05130   0.04360  -0.0287   0.4774   1.0000
   4.250   0.5433   0.05015   0.04236  -0.0290   0.4766   1.0000
   4.500   0.5936   0.04864   0.04076  -0.0297   0.4761   1.0000
   6.750   0.3499   0.09908   0.09143  -0.0290   0.4876   1.0000
   7.000   0.3653   0.10079   0.09312  -0.0291   0.4819   1.0000
   7.250   0.3942   0.10283   0.09513  -0.0297   0.4786   1.0000
   7.500   0.4340   0.10570   0.09798  -0.0309   0.4766   1.0000
   7.750   0.3948   0.10713   0.09943  -0.0292   0.4673   1.0000
   8.000   0.4164   0.10892   0.10121  -0.0295   0.4620   1.0000
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