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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 100,000
Max Cl/Cd: 61.45 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe359-il-100000.txt
Download as CSV file: xf-goe359-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2678   0.09579   0.09145  -0.0263   1.0000   0.0507
  -7.000  -0.2707   0.09385   0.08962  -0.0250   1.0000   0.0518
  -6.750  -0.2750   0.09209   0.08797  -0.0238   1.0000   0.0529
  -6.500  -0.2846   0.09090   0.08690  -0.0218   1.0000   0.0537
  -6.250  -0.2976   0.09008   0.08619  -0.0193   1.0000   0.0543
  -6.000  -0.3093   0.08917   0.08537  -0.0174   1.0000   0.0550
  -5.750  -0.3180   0.08805   0.08432  -0.0165   1.0000   0.0560
  -5.500  -0.2458   0.08425   0.08030  -0.0438   0.9884   0.0598
  -5.250  -0.2384   0.07781   0.07397  -0.0386   0.9844   0.0618
  -5.000  -0.2062   0.07362   0.06973  -0.0437   0.9757   0.0680
  -4.750  -0.1559   0.06843   0.06439  -0.0569   0.9658   0.0745
  -4.500  -0.1152   0.06424   0.06013  -0.0634   0.9588   0.0827
  -4.250  -0.0743   0.05965   0.05542  -0.0713   0.9485   0.0889
  -4.000  -0.0211   0.05552   0.05105  -0.0818   0.9395   0.1008
  -3.750   0.0243   0.05151   0.04688  -0.0886   0.9327   0.1150
  -3.500   0.0665   0.04796   0.04317  -0.0943   0.9236   0.1293
  -3.250   0.1111   0.04408   0.03919  -0.0996   0.9181   0.1452
  -3.000   0.1471   0.04121   0.03623  -0.1028   0.9081   0.1644
  -2.750   0.1927   0.03819   0.03304  -0.1077   0.9021   0.1956
  -2.500   0.2306   0.03626   0.03086  -0.1111   0.8902   0.2311
  -2.250   0.2548   0.01593   0.01093  -0.1049   0.8467   0.2643
  -2.000   0.2757   0.01424   0.00921  -0.1041   0.8344   0.3086
  -1.500   0.3988   0.02596   0.01861  -0.1211   0.8460   0.1429
  -1.250   0.4337   0.02394   0.01593  -0.1210   0.8337   0.1127
  -1.000   0.4627   0.02246   0.01427  -0.1208   0.8211   0.1085
  -0.750   0.4919   0.02161   0.01312  -0.1203   0.8086   0.1098
  -0.500   0.5210   0.02074   0.01198  -0.1198   0.7968   0.1083
  -0.250   0.5495   0.02001   0.01105  -0.1192   0.7853   0.1070
   0.000   0.5760   0.01952   0.01042  -0.1184   0.7725   0.1074
   0.250   0.6023   0.01912   0.00994  -0.1176   0.7601   0.1094
   0.500   0.6287   0.01881   0.00955  -0.1168   0.7484   0.1128
   0.750   0.6548   0.01845   0.00921  -0.1161   0.7379   0.1220
   1.000   0.6823   0.01821   0.00891  -0.1154   0.7270   0.1392
   1.250   0.7087   0.01781   0.00875  -0.1149   0.7145   0.2042
   1.500   0.7353   0.01631   0.00855  -0.1140   0.7024   1.0000
   1.750   0.7612   0.01648   0.00848  -0.1131   0.6902   1.0000
   2.000   0.7873   0.01662   0.00842  -0.1123   0.6780   1.0000
   2.250   0.8141   0.01676   0.00836  -0.1116   0.6671   1.0000
   2.500   0.8396   0.01701   0.00852  -0.1110   0.6557   1.0000
   2.750   0.8649   0.01733   0.00877  -0.1104   0.6451   1.0000
   3.000   0.8912   0.01759   0.00893  -0.1099   0.6356   1.0000
   3.250   0.9175   0.01784   0.00910  -0.1094   0.6258   1.0000
   3.500   0.9423   0.01819   0.00946  -0.1088   0.6151   1.0000
   3.750   0.9683   0.01849   0.00972  -0.1083   0.6058   1.0000
   4.000   0.9946   0.01876   0.00993  -0.1079   0.5964   1.0000
   4.250   1.0190   0.01912   0.01033  -0.1072   0.5854   1.0000
   4.500   1.0442   0.01943   0.01067  -0.1066   0.5749   1.0000
   4.750   1.0708   0.01965   0.01083  -0.1061   0.5649   1.0000
   5.000   1.0953   0.01995   0.01117  -0.1054   0.5531   1.0000
   5.250   1.1195   0.02025   0.01152  -0.1046   0.5406   1.0000
   5.500   1.1438   0.02048   0.01182  -0.1037   0.5272   1.0000
   5.750   1.1680   0.02065   0.01199  -0.1028   0.5125   1.0000
   6.000   1.1919   0.02066   0.01196  -0.1016   0.4956   1.0000
   6.250   1.2132   0.02057   0.01183  -0.1000   0.4735   1.0000
   6.500   1.2345   0.02049   0.01171  -0.0985   0.4512   1.0000
   6.750   1.2539   0.02059   0.01184  -0.0968   0.4279   1.0000
   7.000   1.2735   0.02073   0.01192  -0.0952   0.4053   1.0000
   7.250   1.2930   0.02104   0.01231  -0.0938   0.3835   1.0000
   7.500   1.3118   0.02135   0.01266  -0.0923   0.3604   1.0000
   7.750   1.3308   0.02177   0.01313  -0.0909   0.3383   1.0000
   8.000   1.3499   0.02227   0.01365  -0.0896   0.3201   1.0000
   8.250   1.3685   0.02284   0.01427  -0.0882   0.3007   1.0000
   8.500   1.3829   0.02359   0.01491  -0.0863   0.2738   1.0000
   9.000   1.4113   0.02538   0.01667  -0.0825   0.2342   1.0000
   9.250   1.4260   0.02627   0.01766  -0.0807   0.2195   1.0000
   9.500   1.4380   0.02731   0.01877  -0.0786   0.1970   1.0000
   9.750   1.4467   0.02854   0.02001  -0.0762   0.1603   1.0000
  10.000   1.4396   0.03070   0.02177  -0.0722   0.1070   1.0000
  10.250   1.4246   0.03373   0.02436  -0.0680   0.0628   1.0000
  10.500   1.4159   0.03654   0.02713  -0.0648   0.0529   1.0000
  10.750   1.4120   0.03915   0.02990  -0.0626   0.0464   1.0000
  11.000   1.4036   0.04236   0.03324  -0.0607   0.0429   1.0000
  11.250   1.4021   0.04507   0.03618  -0.0595   0.0401   1.0000
  11.500   1.3979   0.04823   0.03952  -0.0586   0.0380   1.0000
  11.750   1.3917   0.05175   0.04324  -0.0580   0.0368   1.0000
  12.000   1.3842   0.05560   0.04726  -0.0577   0.0360   1.0000
  12.250   1.3754   0.05974   0.05156  -0.0578   0.0353   1.0000
  12.500   1.3659   0.06410   0.05607  -0.0580   0.0348   1.0000
  12.750   1.3561   0.06853   0.06065  -0.0583   0.0344   1.0000
  13.000   1.3468   0.07289   0.06513  -0.0585   0.0340   1.0000
  13.250   1.3401   0.07676   0.06907  -0.0583   0.0336   1.0000
  13.500   1.3405   0.07957   0.07196  -0.0574   0.0333   1.0000
  13.750   1.3470   0.08139   0.07384  -0.0556   0.0329   1.0000
  14.000   1.3609   0.08219   0.07469  -0.0528   0.0326   1.0000
  14.250   1.3802   0.08275   0.07532  -0.0494   0.0325   1.0000
  14.500   1.3932   0.08471   0.07747  -0.0473   0.0323   1.0000
  14.750   1.3973   0.08791   0.08089  -0.0465   0.0320   1.0000
  15.000   1.3959   0.09182   0.08504  -0.0465   0.0317   1.0000
  15.250   1.3906   0.09626   0.08973  -0.0471   0.0316   1.0000
  15.500   1.3826   0.10119   0.09491  -0.0482   0.0315   1.0000
  15.750   1.3722   0.10660   0.10057  -0.0499   0.0316   1.0000
  16.000   1.3597   0.11250   0.10670  -0.0522   0.0317   1.0000
  16.250   1.3458   0.11881   0.11325  -0.0551   0.0319   1.0000
  16.500   1.3305   0.12565   0.12030  -0.0587   0.0322   1.0000
  16.750   1.3147   0.13291   0.12776  -0.0628   0.0324   1.0000
  17.000   1.2984   0.14062   0.13566  -0.0675   0.0327   1.0000
  17.250   1.2821   0.14874   0.14394  -0.0727   0.0330   1.0000
  17.500   1.2665   0.15713   0.15246  -0.0781   0.0333   1.0000
  17.750   1.2508   0.16617   0.16166  -0.0844   0.0337   1.0000
  18.000   1.1638   0.20602   0.20159  -0.1123   0.0413   1.0000
  18.250   1.1671   0.21071   0.20628  -0.1142   0.0425   1.0000
  18.500   1.1576   0.22840   0.22387  -0.1234   0.0556   1.0000
  18.750   0.8376   0.20060   0.19639  -0.0835   0.0500   1.0000
  19.000   0.8396   0.20449   0.20029  -0.0842   0.0527   1.0000
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