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GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 670 AIRFOIL (goe670-il)
Reynolds number: 50,000
Max Cl/Cd: 37.23 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe670-il-50000-n5.txt
Download as CSV file: xf-goe670-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 670 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4038   0.10632   0.09918  -0.0335   1.0000   0.1322
  -8.500  -0.4191   0.10459   0.09757  -0.0334   1.0000   0.1326
  -8.250  -0.4350   0.10270   0.09581  -0.0328   1.0000   0.1328
  -8.000  -0.4449   0.10009   0.09328  -0.0328   1.0000   0.1329
  -7.500  -0.4475   0.08763   0.08078  -0.0346   1.0000   0.0868
  -7.250  -0.4460   0.08470   0.07788  -0.0328   1.0000   0.0854
  -7.000  -0.4501   0.08157   0.07477  -0.0323   1.0000   0.0849
  -6.750  -0.4538   0.07829   0.07148  -0.0324   1.0000   0.0849
  -6.500  -0.4559   0.07483   0.06799  -0.0327   1.0000   0.0852
  -6.250  -0.4557   0.07126   0.06434  -0.0330   1.0000   0.0854
  -6.000  -0.4527   0.06774   0.06073  -0.0329   1.0000   0.0850
  -5.750  -0.4476   0.06423   0.05712  -0.0328   1.0000   0.0841
  -5.500  -0.4407   0.06058   0.05331  -0.0329   1.0000   0.0833
  -5.250  -0.4318   0.05696   0.04949  -0.0330   1.0000   0.0827
  -5.000  -0.4207   0.05339   0.04567  -0.0332   1.0000   0.0823
  -4.750  -0.4077   0.04999   0.04198  -0.0331   1.0000   0.0823
  -4.500  -0.3929   0.04691   0.03855  -0.0330   1.0000   0.0835
  -4.250  -0.3762   0.04379   0.03489  -0.0330   1.0000   0.0861
  -4.000  -0.3578   0.04100   0.03153  -0.0327   0.9999   0.0874
  -3.750  -0.3262   0.03843   0.02857  -0.0347   0.9949   0.0884
  -3.500  -0.2951   0.03650   0.02636  -0.0364   0.9895   0.0899
  -3.250  -0.2624   0.03484   0.02438  -0.0381   0.9842   0.0918
  -3.000  -0.2304   0.03335   0.02255  -0.0395   0.9784   0.0947
  -2.750  -0.1969   0.03212   0.02083  -0.0409   0.9725   0.1007
  -2.500  -0.1640   0.03103   0.01954  -0.0423   0.9667   0.1057
  -2.250  -0.1322   0.03008   0.01838  -0.0434   0.9604   0.1104
  -2.000  -0.0965   0.02918   0.01712  -0.0449   0.9549   0.1167
  -1.750  -0.0655   0.02858   0.01652  -0.0459   0.9479   0.1265
  -1.500  -0.0288   0.02800   0.01579  -0.0477   0.9425   0.1373
  -1.250   0.0029   0.02753   0.01520  -0.0485   0.9353   0.1499
  -1.000   0.0395   0.02713   0.01481  -0.0505   0.9297   0.1679
  -0.750   0.0684   0.02680   0.01450  -0.0509   0.9216   0.1850
  -0.500   0.1042   0.02650   0.01427  -0.0527   0.9158   0.2113
  -0.250   0.1305   0.02623   0.01415  -0.0527   0.9069   0.2416
   0.000   0.1657   0.02571   0.01400  -0.0545   0.9011   0.3054
   0.500   0.2560   0.02412   0.01398  -0.0612   0.8888   1.0000
   0.750   0.2855   0.02436   0.01403  -0.0616   0.8794   1.0000
   1.000   0.3212   0.02454   0.01403  -0.0631   0.8711   1.0000
   1.250   0.3474   0.02475   0.01412  -0.0628   0.8596   1.0000
   1.500   0.3788   0.02489   0.01417  -0.0634   0.8497   1.0000
   1.750   0.4168   0.02485   0.01406  -0.0649   0.8399   1.0000
   2.000   0.4498   0.02467   0.01383  -0.0652   0.8254   1.0000
   2.250   0.4874   0.02422   0.01335  -0.0659   0.8095   1.0000
   2.500   0.5238   0.02373   0.01284  -0.0663   0.7931   1.0000
   2.750   0.5544   0.02344   0.01253  -0.0659   0.7774   1.0000
   3.000   0.5819   0.02333   0.01245  -0.0652   0.7628   1.0000
   3.250   0.6092   0.02321   0.01236  -0.0644   0.7477   1.0000
   3.500   0.6352   0.02313   0.01233  -0.0635   0.7316   1.0000
   3.750   0.6599   0.02306   0.01231  -0.0622   0.7136   1.0000
   4.000   0.6874   0.02292   0.01222  -0.0614   0.6948   1.0000
   4.250   0.7186   0.02269   0.01204  -0.0610   0.6753   1.0000
   4.500   0.7489   0.02252   0.01190  -0.0604   0.6530   1.0000
   4.750   0.7794   0.02242   0.01179  -0.0599   0.6275   1.0000
   5.000   0.8051   0.02252   0.01191  -0.0588   0.5984   1.0000
   5.250   0.8278   0.02273   0.01212  -0.0572   0.5655   1.0000
   5.500   0.8471   0.02305   0.01243  -0.0552   0.5288   1.0000
   5.750   0.8669   0.02341   0.01271  -0.0533   0.4908   1.0000
   6.000   0.8882   0.02386   0.01301  -0.0516   0.4570   1.0000
   6.250   0.9089   0.02447   0.01346  -0.0501   0.4280   1.0000
   6.500   0.9301   0.02518   0.01408  -0.0489   0.4046   1.0000
   6.750   0.9523   0.02595   0.01481  -0.0479   0.3850   1.0000
   7.000   0.9755   0.02675   0.01564  -0.0471   0.3681   1.0000
   7.250   0.9986   0.02757   0.01648  -0.0463   0.3522   1.0000
   7.500   1.0205   0.02839   0.01735  -0.0454   0.3364   1.0000
   7.750   1.0405   0.02921   0.01822  -0.0441   0.3205   1.0000
   8.000   1.0601   0.03004   0.01919  -0.0429   0.3058   1.0000
   8.250   1.0807   0.03093   0.02024  -0.0418   0.2931   1.0000
   8.500   1.0986   0.03181   0.02126  -0.0403   0.2791   1.0000
   8.750   1.1080   0.03261   0.02211  -0.0376   0.2606   1.0000
   9.000   1.1126   0.03340   0.02288  -0.0343   0.2409   1.0000
   9.250   1.1133   0.03425   0.02382  -0.0305   0.2213   1.0000
   9.500   1.1126   0.03519   0.02488  -0.0267   0.2015   1.0000
   9.750   1.1121   0.03626   0.02608  -0.0233   0.1807   1.0000
  10.000   1.1133   0.03751   0.02750  -0.0203   0.1551   1.0000
  10.250   1.1119   0.03912   0.02906  -0.0176   0.1253   1.0000
  10.500   1.1081   0.04133   0.03102  -0.0151   0.1008   1.0000
  10.750   1.1042   0.04398   0.03347  -0.0129   0.0859   1.0000
  11.000   1.1021   0.04669   0.03619  -0.0110   0.0765   1.0000
  11.250   1.1012   0.04942   0.03900  -0.0094   0.0692   1.0000
  11.500   1.0997   0.05219   0.04185  -0.0081   0.0638   1.0000
  11.750   1.0984   0.05507   0.04484  -0.0070   0.0597   1.0000
  12.000   1.0987   0.05794   0.04791  -0.0061   0.0562   1.0000
  12.250   1.0981   0.06096   0.05106  -0.0053   0.0539   1.0000
  12.500   1.0967   0.06410   0.05428  -0.0049   0.0520   1.0000
  12.750   1.0966   0.06730   0.05764  -0.0045   0.0504   1.0000
  13.000   1.0949   0.07092   0.06155  -0.0044   0.0482   1.0000
  13.250   1.0917   0.07475   0.06560  -0.0047   0.0466   1.0000
  13.500   1.0872   0.07881   0.06986  -0.0053   0.0453   1.0000
  13.750   1.0818   0.08309   0.07431  -0.0062   0.0442   1.0000
  14.000   1.0764   0.08751   0.07887  -0.0073   0.0432   1.0000
  14.250   1.0704   0.09220   0.08372  -0.0087   0.0426   1.0000
  14.500   1.0636   0.09723   0.08889  -0.0103   0.0420   1.0000
  14.750   1.0543   0.10292   0.09477  -0.0126   0.0417   1.0000
  15.000   1.0402   0.10988   0.10194  -0.0161   0.0417   1.0000
  15.250   1.0189   0.11894   0.11126  -0.0214   0.0419   1.0000
  15.500   0.9636   0.13900   0.13166  -0.0342   0.0441   1.0000
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