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GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il)
Reynolds number: 50,000
Max Cl/Cd: 32.99 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe677-il-50000-n5.txt
Download as CSV file: xf-goe677-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 677 (= M 6) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5392   0.11358   0.10631  -0.0157   1.0000   0.0853
 -10.250  -0.5379   0.10894   0.10167  -0.0177   1.0000   0.0851
 -10.000  -0.5389   0.10406   0.09682  -0.0202   1.0000   0.0850
  -9.750  -0.5392   0.09923   0.09201  -0.0225   1.0000   0.0847
  -9.500  -0.5394   0.09444   0.08725  -0.0248   1.0000   0.0841
  -9.250  -0.5421   0.08954   0.08238  -0.0273   1.0000   0.0832
  -9.000  -0.5494   0.08466   0.07751  -0.0294   1.0000   0.0823
  -8.750  -0.5603   0.08007   0.07291  -0.0304   1.0000   0.0815
  -8.500  -0.5701   0.07540   0.06818  -0.0312   1.0000   0.0808
  -8.250  -0.5781   0.07083   0.06350  -0.0314   1.0000   0.0802
  -8.000  -0.5837   0.06650   0.05901  -0.0311   1.0000   0.0800
  -7.750  -0.5869   0.06249   0.05480  -0.0303   1.0000   0.0807
  -7.500  -0.5879   0.05872   0.05077  -0.0290   1.0000   0.0818
  -7.250  -0.5870   0.05513   0.04686  -0.0273   1.0000   0.0828
  -7.000  -0.5835   0.05181   0.04319  -0.0254   1.0000   0.0834
  -6.750  -0.5775   0.04880   0.03986  -0.0232   1.0000   0.0836
  -6.500  -0.5704   0.04609   0.03682  -0.0209   1.0000   0.0840
  -6.250  -0.5627   0.04365   0.03405  -0.0184   1.0000   0.0844
  -6.000  -0.5548   0.04151   0.03156  -0.0158   1.0000   0.0850
  -5.750  -0.5469   0.03971   0.02955  -0.0132   1.0000   0.0861
  -5.500  -0.5384   0.03846   0.02825  -0.0109   1.0000   0.0880
  -5.250  -0.5116   0.03693   0.02657  -0.0119   0.9926   0.0911
  -5.000  -0.4760   0.03495   0.02420  -0.0142   0.9816   0.0940
  -4.750  -0.4387   0.03302   0.02183  -0.0164   0.9716   0.0963
  -4.500  -0.4011   0.03135   0.01971  -0.0185   0.9614   0.0989
  -4.250  -0.3643   0.03008   0.01841  -0.0208   0.9517   0.1035
  -4.000  -0.3232   0.02898   0.01711  -0.0236   0.9442   0.1102
  -3.750  -0.2854   0.02789   0.01586  -0.0255   0.9345   0.1153
  -3.500  -0.2442   0.02696   0.01489  -0.0281   0.9269   0.1227
  -3.250  -0.2056   0.02619   0.01404  -0.0303   0.9177   0.1335
  -3.000  -0.1672   0.02542   0.01317  -0.0323   0.9091   0.1449
  -2.750  -0.1312   0.02461   0.01240  -0.0339   0.8993   0.1620
  -2.500  -0.1006   0.02382   0.01171  -0.0345   0.8869   0.1858
  -2.250  -0.0738   0.02290   0.01115  -0.0344   0.8742   0.2323
  -2.000   0.0011   0.02079   0.01169  -0.0399   0.8699   0.8642
  -1.750   0.1351   0.02106   0.01140  -0.0582   0.8677   1.0000
  -1.500   0.1593   0.02105   0.01116  -0.0578   0.8536   1.0000
  -1.250   0.1828   0.02107   0.01096  -0.0572   0.8403   1.0000
  -1.000   0.2061   0.02111   0.01082  -0.0566   0.8277   1.0000
  -0.750   0.2293   0.02115   0.01069  -0.0558   0.8160   1.0000
  -0.500   0.2525   0.02120   0.01058  -0.0550   0.8051   1.0000
  -0.250   0.2751   0.02130   0.01057  -0.0542   0.7931   1.0000
   0.000   0.2978   0.02141   0.01055  -0.0534   0.7820   1.0000
   0.250   0.3208   0.02148   0.01050  -0.0524   0.7720   1.0000
   0.500   0.3431   0.02165   0.01059  -0.0515   0.7606   1.0000
   0.750   0.3654   0.02181   0.01069  -0.0506   0.7497   1.0000
   1.000   0.3883   0.02193   0.01071  -0.0495   0.7401   1.0000
   1.250   0.4103   0.02215   0.01089  -0.0486   0.7287   1.0000
   1.500   0.4324   0.02237   0.01108  -0.0476   0.7178   1.0000
   1.750   0.4559   0.02251   0.01116  -0.0466   0.7084   1.0000
   2.000   0.4779   0.02280   0.01145  -0.0457   0.6968   1.0000
   2.250   0.5001   0.02309   0.01174  -0.0448   0.6859   1.0000
   2.500   0.5234   0.02325   0.01186  -0.0437   0.6768   1.0000
   2.750   0.5446   0.02363   0.01227  -0.0427   0.6649   1.0000
   3.000   0.5662   0.02397   0.01264  -0.0417   0.6541   1.0000
   3.250   0.5893   0.02416   0.01282  -0.0405   0.6452   1.0000
   3.500   0.6097   0.02461   0.01334  -0.0395   0.6334   1.0000
   3.750   0.6307   0.02500   0.01379  -0.0384   0.6228   1.0000
   4.000   0.6535   0.02523   0.01403  -0.0372   0.6138   1.0000
   4.250   0.6729   0.02574   0.01463  -0.0360   0.6021   1.0000
   4.500   0.6935   0.02613   0.01509  -0.0348   0.5916   1.0000
   4.750   0.7158   0.02635   0.01538  -0.0335   0.5822   1.0000
   5.000   0.7342   0.02685   0.01599  -0.0321   0.5701   1.0000
   5.250   0.7538   0.02721   0.01644  -0.0306   0.5584   1.0000
   5.500   0.7745   0.02737   0.01668  -0.0291   0.5466   1.0000
   5.750   0.7955   0.02740   0.01677  -0.0274   0.5338   1.0000
   6.000   0.8155   0.02743   0.01687  -0.0256   0.5196   1.0000
   6.250   0.8341   0.02751   0.01703  -0.0237   0.5037   1.0000
   6.500   0.8525   0.02759   0.01720  -0.0217   0.4872   1.0000
   6.750   0.8709   0.02766   0.01733  -0.0197   0.4700   1.0000
   7.000   0.8890   0.02775   0.01747  -0.0177   0.4519   1.0000
   7.250   0.9070   0.02791   0.01764  -0.0156   0.4335   1.0000
   7.500   0.9245   0.02816   0.01794  -0.0136   0.4151   1.0000
   7.750   0.9412   0.02853   0.01833  -0.0115   0.3967   1.0000
   8.000   0.9538   0.02915   0.01908  -0.0092   0.3762   1.0000
   8.250   0.9660   0.02977   0.01982  -0.0069   0.3547   1.0000
   8.500   0.9778   0.03040   0.02051  -0.0045   0.3326   1.0000
   8.750   0.9868   0.03120   0.02143  -0.0019   0.3079   1.0000
   9.000   0.9945   0.03207   0.02228   0.0008   0.2827   1.0000
   9.250   1.0004   0.03307   0.02316   0.0036   0.2594   1.0000
   9.500   1.0047   0.03433   0.02434   0.0064   0.2378   1.0000
   9.750   1.0080   0.03570   0.02561   0.0091   0.2205   1.0000
  10.000   1.0113   0.03714   0.02700   0.0117   0.2067   1.0000
  10.250   1.0173   0.03864   0.02847   0.0139   0.1955   1.0000
  10.500   1.0250   0.04012   0.02990   0.0158   0.1856   1.0000
  10.750   1.0329   0.04175   0.03167   0.0174   0.1755   1.0000
  11.000   1.0410   0.04340   0.03337   0.0189   0.1664   1.0000
  11.250   1.0466   0.04510   0.03506   0.0203   0.1569   1.0000
  11.500   1.0447   0.04734   0.03746   0.0215   0.1464   1.0000
  11.750   1.0410   0.04977   0.03993   0.0223   0.1361   1.0000
  12.000   1.0368   0.05232   0.04246   0.0227   0.1264   1.0000
  12.250   1.0319   0.05524   0.04550   0.0228   0.1169   1.0000
  12.500   1.0298   0.05814   0.04852   0.0229   0.1089   1.0000
  12.750   1.0282   0.06089   0.05126   0.0231   0.1017   1.0000
  13.000   1.0250   0.06425   0.05484   0.0230   0.0942   1.0000
  13.250   1.0236   0.06718   0.05767   0.0231   0.0875   1.0000
  13.500   1.0180   0.07111   0.06188   0.0227   0.0807   1.0000
  13.750   1.0174   0.07404   0.06466   0.0227   0.0749   1.0000
  14.000   1.0084   0.07885   0.06986   0.0217   0.0701   1.0000
  14.250   1.0025   0.08307   0.07425   0.0209   0.0661   1.0000
  14.500   1.0034   0.08604   0.07713   0.0207   0.0627   1.0000
  14.750   0.9890   0.09221   0.08366   0.0185   0.0607   1.0000
  15.000   0.9727   0.09893   0.09066   0.0157   0.0591   1.0000
  15.250   0.9535   0.10659   0.09857   0.0121   0.0581   1.0000
  15.500   0.9280   0.11612   0.10832   0.0072   0.0578   1.0000
  15.750   0.8932   0.12884   0.12121   0.0004   0.0584   1.0000
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