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GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 402 AIRFOIL (goe402-il)
Reynolds number: 200,000
Max Cl/Cd: 75.66 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe402-il-200000.txt
Download as CSV file: xf-goe402-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2783   0.09227   0.08901  -0.0211   1.0000   0.0249
  -7.250  -0.2787   0.09019   0.08699  -0.0207   1.0000   0.0253
  -7.000  -0.2806   0.08823   0.08511  -0.0201   1.0000   0.0258
  -6.750  -0.2782   0.08602   0.08296  -0.0208   1.0000   0.0263
  -6.500  -0.2749   0.08406   0.08107  -0.0223   1.0000   0.0269
  -6.250  -0.2709   0.08239   0.07946  -0.0245   1.0000   0.0272
  -6.000  -0.2715   0.08131   0.07846  -0.0258   0.9999   0.0274
  -5.750  -0.2152   0.07660   0.07362  -0.0411   0.9912   0.0277
  -5.500  -0.1753   0.07038   0.06734  -0.0500   0.9839   0.0280
  -5.250  -0.1577   0.06472   0.06173  -0.0509   0.9750   0.0287
  -5.000  -0.1254   0.06030   0.05727  -0.0556   0.9652   0.0298
  -4.750  -0.0837   0.05598   0.05286  -0.0630   0.9561   0.0319
  -4.500  -0.0282   0.05231   0.04898  -0.0731   0.9409   0.0359
  -4.250   0.0294   0.04949   0.04576  -0.0817   0.9225   0.0367
  -4.000   0.0540   0.04333   0.03960  -0.0850   0.9046   0.0378
  -3.750   0.0827   0.03998   0.03615  -0.0874   0.8843   0.0394
  -3.500   0.1134   0.03728   0.03325  -0.0896   0.8616   0.0420
  -3.250   0.1609   0.03663   0.03189  -0.0922   0.8420   0.0477
  -3.000   0.1775   0.03196   0.02724  -0.0929   0.8250   0.0498
  -2.750   0.2006   0.03003   0.02516  -0.0929   0.8088   0.0528
  -2.500   0.2357   0.02887   0.02334  -0.0933   0.7947   0.0606
  -2.250   0.2555   0.02612   0.02062  -0.0933   0.7811   0.0638
  -2.000   0.2832   0.02473   0.01884  -0.0932   0.7680   0.0755
  -1.750   0.3087   0.02358   0.01745  -0.0930   0.7549   0.0893
  -1.500   0.3335   0.02232   0.01603  -0.0928   0.7424   0.1038
  -1.250   0.3575   0.02105   0.01468  -0.0926   0.7306   0.1203
   0.000   0.4991   0.01558   0.00759  -0.0888   0.6734   0.0854
   0.250   0.5265   0.01468   0.00643  -0.0880   0.6625   0.0768
   0.500   0.5534   0.01448   0.00605  -0.0872   0.6504   0.0739
   0.750   0.5795   0.01397   0.00548  -0.0865   0.6373   0.0732
   1.000   0.6050   0.01336   0.00486  -0.0859   0.6238   0.0755
   1.250   0.6305   0.01300   0.00450  -0.0851   0.6097   0.0770
   1.500   0.6559   0.01276   0.00422  -0.0844   0.5951   0.0779
   1.750   0.6813   0.01260   0.00402  -0.0837   0.5800   0.0802
   2.000   0.7067   0.01254   0.00386  -0.0830   0.5639   0.0840
   2.250   0.7319   0.01252   0.00375  -0.0823   0.5463   0.0911
   2.500   0.7556   0.01206   0.00383  -0.0816   0.5276   0.3527
   2.750   0.7904   0.01107   0.00380  -0.0829   0.5076   1.0000
   3.000   0.8153   0.01132   0.00386  -0.0822   0.4903   1.0000
   3.250   0.8402   0.01158   0.00397  -0.0815   0.4739   1.0000
   3.500   0.8653   0.01184   0.00411  -0.0810   0.4592   1.0000
   3.750   0.8904   0.01213   0.00427  -0.0804   0.4465   1.0000
   4.000   0.9157   0.01239   0.00450  -0.0799   0.4349   1.0000
   4.250   0.9411   0.01268   0.00474  -0.0795   0.4250   1.0000
   4.500   0.9663   0.01301   0.00497  -0.0790   0.4167   1.0000
   4.750   0.9919   0.01328   0.00526  -0.0786   0.4082   1.0000
   5.000   1.0173   0.01363   0.00557  -0.0782   0.4014   1.0000
   5.250   1.0426   0.01392   0.00589  -0.0778   0.3939   1.0000
   5.500   1.0681   0.01431   0.00622  -0.0774   0.3880   1.0000
   5.750   1.0934   0.01461   0.00660  -0.0770   0.3814   1.0000
   6.000   1.1187   0.01499   0.00698  -0.0766   0.3756   1.0000
   6.250   1.1437   0.01533   0.00741  -0.0762   0.3694   1.0000
   6.500   1.1687   0.01567   0.00779  -0.0758   0.3629   1.0000
   6.750   1.1935   0.01607   0.00824  -0.0753   0.3569   1.0000
   7.000   1.2182   0.01641   0.00871  -0.0748   0.3506   1.0000
   7.250   1.2423   0.01679   0.00914  -0.0743   0.3430   1.0000
   7.500   1.2647   0.01707   0.00941  -0.0735   0.3308   1.0000
   7.750   1.2865   0.01726   0.00974  -0.0725   0.3186   1.0000
   8.000   1.3081   0.01748   0.01011  -0.0715   0.3061   1.0000
   8.250   1.3285   0.01767   0.01038  -0.0704   0.2899   1.0000
   8.500   1.3489   0.01791   0.01070  -0.0693   0.2731   1.0000
   8.750   1.3694   0.01810   0.01105  -0.0681   0.2483   1.0000
   9.000   1.3831   0.01887   0.01155  -0.0662   0.1791   1.0000
   9.250   1.3782   0.02165   0.01360  -0.0623   0.0814   1.0000
   9.500   1.3713   0.02442   0.01598  -0.0580   0.0416   1.0000
   9.750   1.3778   0.02583   0.01754  -0.0552   0.0357   1.0000
  10.000   1.3733   0.02766   0.01947  -0.0510   0.0320   1.0000
  10.250   1.3759   0.02907   0.02103  -0.0481   0.0301   1.0000
  10.500   1.3754   0.03079   0.02288  -0.0452   0.0284   1.0000
  10.750   1.3730   0.03281   0.02504  -0.0428   0.0273   1.0000
  11.000   1.3692   0.03520   0.02754  -0.0409   0.0264   1.0000
  11.250   1.3643   0.03796   0.03041  -0.0396   0.0256   1.0000
  11.500   1.3582   0.04110   0.03364  -0.0386   0.0250   1.0000
  11.750   1.3517   0.04446   0.03707  -0.0376   0.0243   1.0000
  12.000   1.3484   0.04766   0.04031  -0.0362   0.0236   1.0000
  12.250   1.3530   0.05005   0.04286  -0.0355   0.0231   1.0000
  12.500   1.3572   0.05253   0.04549  -0.0350   0.0223   1.0000
  12.750   1.3614   0.05507   0.04815  -0.0344   0.0215   1.0000
  13.000   1.3672   0.05761   0.05082  -0.0335   0.0210   1.0000
  13.250   1.3735   0.06029   0.05365  -0.0326   0.0206   1.0000
  13.500   1.3784   0.06323   0.05677  -0.0319   0.0203   1.0000
  13.750   1.3812   0.06655   0.06029  -0.0314   0.0201   1.0000
  14.000   1.3815   0.07028   0.06425  -0.0313   0.0201   1.0000
  14.250   1.3780   0.07454   0.06874  -0.0316   0.0202   1.0000
  14.500   1.3704   0.07938   0.07385  -0.0324   0.0203   1.0000
  14.750   1.3596   0.08469   0.07941  -0.0338   0.0205   1.0000
  15.000   1.3465   0.09048   0.08545  -0.0358   0.0208   1.0000
  15.250   1.3316   0.09671   0.09192  -0.0384   0.0210   1.0000
  15.500   1.3153   0.10341   0.09884  -0.0416   0.0213   1.0000
  15.750   1.2985   0.11051   0.10615  -0.0453   0.0215   1.0000
  16.000   1.2813   0.11803   0.11387  -0.0496   0.0217   1.0000
  16.250   1.2638   0.12598   0.12201  -0.0545   0.0220   1.0000
  16.500   1.2456   0.13445   0.13064  -0.0598   0.0222   1.0000
  16.750   1.2273   0.14341   0.13976  -0.0657   0.0225   1.0000
  17.000   1.2090   0.15280   0.14929  -0.0719   0.0228   1.0000
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