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GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 402 AIRFOIL (goe402-il)
Reynolds number: 500,000
Max Cl/Cd: 105.71 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe402-il-500000.txt
Download as CSV file: xf-goe402-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 402 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2854   0.08954   0.08748  -0.0201   1.0000   0.0135
  -7.250  -0.2874   0.08762   0.08561  -0.0191   1.0000   0.0137
  -7.000  -0.2910   0.08576   0.08381  -0.0178   1.0000   0.0140
  -6.750  -0.2890   0.08345   0.08153  -0.0181   0.9999   0.0142
  -6.500  -0.2543   0.07866   0.07673  -0.0274   0.9940   0.0158
  -6.250  -0.2085   0.07377   0.07179  -0.0419   0.9841   0.0163
  -6.000  -0.1693   0.06884   0.06679  -0.0526   0.9714   0.0164
  -5.750  -0.1288   0.06387   0.06175  -0.0614   0.9570   0.0165
  -5.500  -0.1028   0.05841   0.05627  -0.0653   0.9352   0.0169
  -5.250  -0.0601   0.05416   0.05186  -0.0731   0.8907   0.0175
  -5.000  -0.0337   0.05121   0.04860  -0.0765   0.8333   0.0182
  -3.750   0.0928   0.03597   0.03236  -0.0871   0.7401   0.0223
  -3.500   0.1167   0.03387   0.03013  -0.0878   0.7292   0.0231
  -3.250   0.1431   0.03165   0.02774  -0.0886   0.7195   0.0243
  -3.000   0.1795   0.02982   0.02557  -0.0891   0.7101   0.0275
  -2.500   0.2313   0.02312   0.01832  -0.0898   0.6922   0.0288
  -2.250   0.2549   0.02200   0.01714  -0.0899   0.6817   0.0303
  -2.000   0.2814   0.02059   0.01555  -0.0898   0.6717   0.0326
  -1.750   0.3129   0.02070   0.01525  -0.0888   0.6622   0.0366
   0.500   0.5514   0.01103   0.00389  -0.0854   0.5576   0.0507
   0.750   0.5784   0.01109   0.00383  -0.0848   0.5435   0.0482
   1.000   0.6046   0.01068   0.00335  -0.0844   0.5299   0.0475
   1.250   0.6308   0.01044   0.00304  -0.0839   0.5153   0.0476
   1.500   0.6567   0.01022   0.00278  -0.0834   0.4997   0.0480
   1.750   0.6821   0.00991   0.00241  -0.0829   0.4831   0.0498
   2.000   0.7079   0.00983   0.00228  -0.0824   0.4648   0.0506
   2.250   0.7336   0.00983   0.00219  -0.0820   0.4442   0.0525
   2.500   0.7594   0.00988   0.00216  -0.0815   0.4231   0.0552
   2.750   0.7851   0.01000   0.00218  -0.0811   0.4050   0.0584
   3.000   0.8108   0.01013   0.00222  -0.0807   0.3899   0.0642
   3.250   0.8428   0.00859   0.00250  -0.0822   0.3770   1.0000
   3.500   0.8685   0.00880   0.00261  -0.0817   0.3669   1.0000
   3.750   0.8939   0.00903   0.00275  -0.0813   0.3585   1.0000
   4.000   0.9198   0.00922   0.00291  -0.0809   0.3511   1.0000
   4.250   0.9452   0.00945   0.00308  -0.0805   0.3447   1.0000
   4.500   0.9712   0.00962   0.00325  -0.0801   0.3388   1.0000
   4.750   0.9965   0.00985   0.00344  -0.0797   0.3331   1.0000
   5.000   1.0223   0.01005   0.00365  -0.0793   0.3286   1.0000
   5.250   1.0481   0.01023   0.00385  -0.0790   0.3238   1.0000
   5.500   1.0734   0.01046   0.00407  -0.0786   0.3191   1.0000
   5.750   1.0987   0.01070   0.00431  -0.0782   0.3151   1.0000
   6.000   1.1246   0.01086   0.00455  -0.0779   0.3110   1.0000
   6.250   1.1495   0.01110   0.00477  -0.0774   0.3039   1.0000
   6.500   1.1752   0.01124   0.00496  -0.0771   0.2949   1.0000
   6.750   1.1998   0.01148   0.00519  -0.0766   0.2863   1.0000
   7.000   1.2253   0.01163   0.00541  -0.0763   0.2774   1.0000
   7.250   1.2503   0.01184   0.00565  -0.0759   0.2685   1.0000
   7.500   1.2749   0.01206   0.00587  -0.0754   0.2530   1.0000
   7.750   1.2983   0.01240   0.00614  -0.0748   0.2311   1.0000
   8.000   1.3193   0.01297   0.00656  -0.0740   0.1906   1.0000
   8.250   1.3322   0.01439   0.00754  -0.0721   0.1269   1.0000
   8.500   1.3486   0.01543   0.00842  -0.0705   0.0952   1.0000
   8.750   1.3538   0.01751   0.01001  -0.0675   0.0256   1.0000
   9.000   1.3703   0.01843   0.01095  -0.0659   0.0197   1.0000
   9.250   1.3847   0.01948   0.01214  -0.0639   0.0170   1.0000
   9.500   1.4006   0.02030   0.01307  -0.0623   0.0160   1.0000
   9.750   1.4142   0.02124   0.01412  -0.0603   0.0150   1.0000
  10.000   1.4250   0.02228   0.01525  -0.0580   0.0137   1.0000
  10.250   1.4283   0.02353   0.01660  -0.0546   0.0130   1.0000
  10.500   1.4230   0.02519   0.01840  -0.0502   0.0125   1.0000
  10.750   1.4138   0.02725   0.02060  -0.0460   0.0120   1.0000
  11.000   1.4159   0.02878   0.02224  -0.0437   0.0119   1.0000
  11.250   1.4165   0.03060   0.02420  -0.0417   0.0117   1.0000
  11.500   1.4171   0.03264   0.02635  -0.0402   0.0114   1.0000
  11.750   1.4160   0.03507   0.02890  -0.0391   0.0111   1.0000
  12.000   1.4142   0.03776   0.03171  -0.0383   0.0108   1.0000
  12.250   1.4118   0.04067   0.03473  -0.0377   0.0106   1.0000
  12.500   1.4096   0.04365   0.03782  -0.0373   0.0104   1.0000
  12.750   1.4078   0.04669   0.04097  -0.0371   0.0102   1.0000
  13.000   1.4059   0.04981   0.04419  -0.0370   0.0099   1.0000
  13.250   1.4043   0.05299   0.04746  -0.0370   0.0097   1.0000
  13.500   1.4027   0.05622   0.05077  -0.0373   0.0094   1.0000
  13.750   1.3998   0.05965   0.05428  -0.0376   0.0091   1.0000
  14.000   1.3969   0.06309   0.05779  -0.0377   0.0088   1.0000
  14.250   1.3944   0.06647   0.06126  -0.0372   0.0086   1.0000
  14.500   1.3946   0.06977   0.06469  -0.0360   0.0084   1.0000
  14.750   1.3912   0.07382   0.06891  -0.0361   0.0083   1.0000
  15.000   1.3870   0.07796   0.07321  -0.0373   0.0083   1.0000
  15.250   1.3815   0.08246   0.07787  -0.0389   0.0082   1.0000
  15.500   1.3750   0.08726   0.08284  -0.0407   0.0082   1.0000
  15.750   1.3675   0.09241   0.08816  -0.0427   0.0081   1.0000
  16.000   1.3595   0.09780   0.09372  -0.0450   0.0081   1.0000
  16.250   1.3500   0.10360   0.09969  -0.0475   0.0081   1.0000
  16.500   1.3394   0.10981   0.10607  -0.0507   0.0081   1.0000
  16.750   1.3280   0.11637   0.11280  -0.0541   0.0081   1.0000
  17.000   1.3160   0.12324   0.11983  -0.0578   0.0081   1.0000
  17.250   1.3033   0.13040   0.12716  -0.0619   0.0081   1.0000
  17.500   1.2902   0.13787   0.13479  -0.0664   0.0081   1.0000
  17.750   1.2768   0.14567   0.14274  -0.0712   0.0081   1.0000
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