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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 500,000
Max Cl/Cd: 95.07 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610b-il-500000-n5.txt
Download as CSV file: xf-goe610b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3364   0.12810   0.12570  -0.0297   1.0000   0.0071
 -11.500  -0.3325   0.12476   0.12238  -0.0305   1.0000   0.0071
 -10.500  -0.3188   0.11165   0.10934  -0.0336   1.0000   0.0071
 -10.250  -0.3112   0.11018   0.10789  -0.0338   1.0000   0.0076
 -10.000  -0.3090   0.10700   0.10473  -0.0344   1.0000   0.0076
  -9.500  -0.2902   0.10113   0.09889  -0.0380   0.9903   0.0082
  -9.250  -0.2791   0.09694   0.09471  -0.0415   0.9795   0.0084
  -9.000  -0.2653   0.09226   0.09002  -0.0463   0.9665   0.0085
  -8.750  -0.2456   0.08698   0.08472  -0.0531   0.9535   0.0086
  -8.500  -0.2205   0.08091   0.07860  -0.0622   0.9386   0.0089
  -8.250  -0.1972   0.07316   0.07077  -0.0739   0.9117   0.0095
  -8.000  -0.1849   0.06876   0.06623  -0.0797   0.8795   0.0102
  -7.750  -0.1761   0.06578   0.06315  -0.0825   0.8596   0.0105
  -7.500  -0.1666   0.06311   0.06039  -0.0846   0.8456   0.0108
  -7.250  -0.1575   0.05986   0.05706  -0.0873   0.8345   0.0114
  -7.000  -0.1496   0.05516   0.05229  -0.0912   0.8248   0.0119
  -6.750  -0.1422   0.04821   0.04519  -0.0967   0.8163   0.0130
  -6.500  -0.1305   0.04084   0.03763  -0.1018   0.8089   0.0142
  -6.250  -0.1085   0.03929   0.03597  -0.1027   0.8028   0.0150
  -6.000  -0.0886   0.03547   0.03198  -0.1045   0.7965   0.0166
  -5.750  -0.0771   0.02596   0.02187  -0.1066   0.7905   0.0197
  -5.500  -0.0512   0.02601   0.02189  -0.1064   0.7846   0.0206
  -5.250  -0.0251   0.02627   0.02212  -0.1063   0.7779   0.0216
  -5.000  -0.0128   0.01774   0.01264  -0.1053   0.7724   0.0291
  -4.750   0.0125   0.01700   0.01169  -0.1048   0.7652   0.0302
  -4.500   0.0365   0.01619   0.01069  -0.1044   0.7580   0.0315
  -4.250   0.0630   0.01637   0.01089  -0.1042   0.7495   0.0323
  -4.000   0.0893   0.01651   0.01101  -0.1039   0.7406   0.0334
  -3.750   0.1149   0.01626   0.01066  -0.1035   0.7301   0.0346
  -3.500   0.1398   0.01559   0.00980  -0.1030   0.7181   0.0359
  -3.250   0.1647   0.01494   0.00894  -0.1024   0.7044   0.0373
  -3.000   0.1892   0.01407   0.00781  -0.1017   0.6889   0.0379
  -2.750   0.2139   0.01334   0.00682  -0.1010   0.6730   0.0383
  -2.250   0.2633   0.01239   0.00541  -0.0996   0.6370   0.0395
  -2.000   0.2882   0.01194   0.00475  -0.0989   0.6208   0.0397
  -1.750   0.3132   0.01158   0.00421  -0.0982   0.6050   0.0402
  -1.500   0.3386   0.01131   0.00380  -0.0977   0.5928   0.0408
  -1.250   0.3644   0.01113   0.00352  -0.0972   0.5822   0.0416
  -1.000   0.3906   0.01103   0.00335  -0.0968   0.5741   0.0423
  -0.750   0.4168   0.01101   0.00325  -0.0964   0.5663   0.0428
  -0.500   0.4421   0.01054   0.00276  -0.0959   0.5607   0.0448
  -0.250   0.4682   0.01039   0.00260  -0.0956   0.5550   0.0460
   0.000   0.4942   0.01030   0.00249  -0.0952   0.5499   0.0471
   0.250   0.5204   0.01021   0.00239  -0.0948   0.5440   0.0480
   0.500   0.5464   0.01014   0.00229  -0.0944   0.5376   0.0487
   0.750   0.5722   0.01009   0.00222  -0.0940   0.5319   0.0494
   1.000   0.5985   0.01002   0.00216  -0.0936   0.5265   0.0499
   1.250   0.6244   0.00998   0.00211  -0.0932   0.5209   0.0503
   1.500   0.6504   0.00997   0.00210  -0.0928   0.5152   0.0512
   1.750   0.6766   0.00996   0.00210  -0.0925   0.5088   0.0521
   2.000   0.7024   0.00997   0.00210  -0.0921   0.5030   0.0526
   2.250   0.7286   0.00994   0.00210  -0.0917   0.4975   0.0527
   2.500   0.7546   0.00995   0.00212  -0.0914   0.4907   0.0528
   2.750   0.7804   0.00997   0.00214  -0.0909   0.4832   0.0529
   3.000   0.8059   0.01001   0.00218  -0.0905   0.4735   0.0531
   3.250   0.8316   0.01004   0.00223  -0.0901   0.4634   0.0538
   3.500   0.8566   0.01012   0.00228  -0.0895   0.4470   0.0553
   3.750   0.8771   0.01045   0.00239  -0.0882   0.3884   0.0575
   4.000   0.8944   0.01109   0.00272  -0.0864   0.3278   0.0631
   4.250   0.9161   0.01137   0.00301  -0.0854   0.3057   0.1171
   5.250   1.0486   0.01103   0.00426  -0.0917   0.2574   1.0000
   5.500   1.0707   0.01129   0.00451  -0.0907   0.2482   1.0000
   5.750   1.0925   0.01156   0.00476  -0.0896   0.2359   1.0000
   6.000   1.1126   0.01194   0.00505  -0.0883   0.2145   1.0000
   6.250   1.1248   0.01282   0.00555  -0.0857   0.1439   1.0000
   6.500   1.1404   0.01348   0.00607  -0.0837   0.1214   1.0000
   6.750   1.1593   0.01390   0.00648  -0.0822   0.1139   1.0000
   7.000   1.1786   0.01428   0.00687  -0.0808   0.1080   1.0000
   7.250   1.1984   0.01462   0.00724  -0.0794   0.1020   1.0000
   7.500   1.2166   0.01505   0.00768  -0.0778   0.0939   1.0000
   7.750   1.2325   0.01559   0.00810  -0.0759   0.0664   1.0000
   8.000   1.2417   0.01651   0.00883  -0.0729   0.0379   1.0000
   8.250   1.2489   0.01737   0.00958  -0.0695   0.0204   1.0000
   8.500   1.2609   0.01796   0.01019  -0.0668   0.0166   1.0000
   8.750   1.2730   0.01858   0.01086  -0.0643   0.0137   1.0000
   9.000   1.2865   0.01913   0.01149  -0.0621   0.0127   1.0000
   9.250   1.2990   0.01977   0.01222  -0.0599   0.0116   1.0000
   9.500   1.3103   0.02051   0.01302  -0.0576   0.0108   1.0000
   9.750   1.3190   0.02145   0.01403  -0.0550   0.0098   1.0000
  10.000   1.3283   0.02239   0.01505  -0.0527   0.0094   1.0000
  10.250   1.3398   0.02321   0.01594  -0.0508   0.0087   1.0000
  10.500   1.3492   0.02422   0.01703  -0.0488   0.0083   1.0000
  10.750   1.3585   0.02528   0.01815  -0.0470   0.0078   1.0000
  11.000   1.3668   0.02646   0.01940  -0.0451   0.0075   1.0000
  11.250   1.3728   0.02786   0.02087  -0.0433   0.0072   1.0000
  11.500   1.3754   0.02962   0.02271  -0.0413   0.0069   1.0000
  11.750   1.3800   0.03127   0.02451  -0.0396   0.0065   1.0000
  12.000   1.3855   0.03290   0.02623  -0.0381   0.0064   1.0000
  12.250   1.3893   0.03474   0.02818  -0.0367   0.0063   1.0000
  12.500   1.3919   0.03674   0.03028  -0.0354   0.0060   1.0000
  12.750   1.3940   0.03887   0.03251  -0.0342   0.0058   1.0000
  13.000   1.3968   0.04098   0.03472  -0.0332   0.0056   1.0000
  13.250   1.4031   0.04279   0.03659  -0.0325   0.0053   1.0000
  13.500   1.4050   0.04511   0.03900  -0.0318   0.0052   1.0000
  13.750   1.4057   0.04765   0.04162  -0.0312   0.0050   1.0000
  14.000   1.4029   0.05067   0.04474  -0.0307   0.0049   1.0000
  14.250   1.3965   0.05421   0.04838  -0.0304   0.0047   1.0000
  14.500   1.3941   0.05740   0.05169  -0.0302   0.0047   1.0000
  14.750   1.3923   0.06060   0.05501  -0.0302   0.0046   1.0000
  15.000   1.3892   0.06405   0.05858  -0.0303   0.0046   1.0000
  15.250   1.3873   0.06746   0.06213  -0.0306   0.0045   1.0000
  15.500   1.3831   0.07119   0.06599  -0.0310   0.0044   1.0000
  15.750   1.3779   0.07520   0.07014  -0.0315   0.0043   1.0000
  16.000   1.3730   0.07926   0.07433  -0.0323   0.0042   1.0000
  16.250   1.3657   0.08376   0.07896  -0.0332   0.0042   1.0000
  16.500   1.3597   0.08817   0.08350  -0.0343   0.0042   1.0000
  16.750   1.3523   0.09293   0.08840  -0.0357   0.0041   1.0000
  17.000   1.3449   0.09787   0.09347  -0.0373   0.0040   1.0000
  17.250   1.3381   0.10287   0.09860  -0.0391   0.0039   1.0000
  17.500   1.3305   0.10809   0.10396  -0.0411   0.0039   1.0000
  17.750   1.3217   0.11369   0.10974  -0.0435   0.0039   1.0000
  18.000   1.3136   0.11934   0.11552  -0.0460   0.0038   1.0000
  18.250   1.3041   0.12537   0.12169  -0.0489   0.0038   1.0000
  18.500   1.2940   0.13158   0.12805  -0.0519   0.0038   1.0000
  18.750   1.2843   0.13786   0.13446  -0.0552   0.0037   1.0000
  19.000   1.2750   0.14419   0.14092  -0.0586   0.0037   1.0000
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