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GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 702 AIRFOIL (goe702-il)
Reynolds number: 200,000
Max Cl/Cd: 57.12 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe702-il-200000.txt
Download as CSV file: xf-goe702-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 702 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1275   0.09798   0.09363  -0.0552   0.7869   0.1020
  -9.750  -0.3154   0.06196   0.05762  -0.0798   0.7898   0.0788
  -9.500  -0.3737   0.05160   0.04720  -0.0863   0.7831   0.0776
  -9.250  -0.4528   0.04059   0.03549  -0.0878   0.7771   0.0769
  -9.000  -0.4700   0.03552   0.02973  -0.0861   0.7718   0.0778
  -8.750  -0.4675   0.03246   0.02611  -0.0845   0.7668   0.0791
  -8.500  -0.4449   0.03155   0.02526  -0.0841   0.7605   0.0803
  -8.250  -0.4229   0.03078   0.02444  -0.0833   0.7551   0.0815
  -8.000  -0.4036   0.02961   0.02307  -0.0823   0.7504   0.0830
  -7.750  -0.3856   0.02815   0.02133  -0.0813   0.7450   0.0848
  -7.500  -0.3680   0.02678   0.01949  -0.0800   0.7391   0.0870
  -7.250  -0.3440   0.02584   0.01860  -0.0795   0.7339   0.0888
  -7.000  -0.3196   0.02534   0.01803  -0.0788   0.7293   0.0908
  -6.750  -0.2959   0.02462   0.01718  -0.0781   0.7235   0.0933
  -6.500  -0.2731   0.02379   0.01602  -0.0772   0.7173   0.0959
  -6.250  -0.2482   0.02294   0.01518  -0.0766   0.7120   0.0984
  -6.000  -0.2227   0.02257   0.01474  -0.0759   0.7070   0.1014
  -5.750  -0.1976   0.02205   0.01408  -0.0753   0.7004   0.1049
  -5.500  -0.1724   0.02125   0.01319  -0.0747   0.6944   0.1081
  -5.250  -0.1462   0.02085   0.01276  -0.0741   0.6891   0.1118
  -5.000  -0.1204   0.02050   0.01227  -0.0735   0.6822   0.1163
  -4.750  -0.0946   0.01980   0.01158  -0.0730   0.6753   0.1205
  -4.500  -0.0679   0.01944   0.01115  -0.0724   0.6697   0.1254
  -4.250  -0.0417   0.01903   0.01061  -0.0718   0.6628   0.1309
  -4.000  -0.0153   0.01854   0.01021  -0.0713   0.6551   0.1363
  -3.750   0.0118   0.01826   0.00974  -0.0707   0.6489   0.1426
  -3.500   0.0379   0.01773   0.00931  -0.0703   0.6405   0.1487
  -3.250   0.0650   0.01744   0.00894  -0.0697   0.6327   0.1554
  -3.000   0.0919   0.01702   0.00848  -0.0692   0.6259   0.1621
  -2.750   0.1185   0.01675   0.00824  -0.0687   0.6162   0.1691
  -2.500   0.1459   0.01639   0.00778  -0.0682   0.6089   0.1764
  -2.250   0.1723   0.01614   0.00760  -0.0677   0.5982   0.1841
  -2.000   0.1996   0.01584   0.00721  -0.0672   0.5900   0.1927
  -1.750   0.2260   0.01564   0.00708  -0.0667   0.5793   0.2022
  -1.500   0.2531   0.01540   0.00680  -0.0662   0.5709   0.2134
  -1.250   0.2797   0.01525   0.00668  -0.0658   0.5599   0.2272
  -1.000   0.3068   0.01510   0.00648  -0.0653   0.5516   0.2449
  -0.750   0.3328   0.01496   0.00647  -0.0647   0.5407   0.2668
  -0.500   0.3595   0.01487   0.00635  -0.0642   0.5328   0.2926
  -0.250   0.3857   0.01486   0.00640  -0.0637   0.5228   0.3182
   0.000   0.4125   0.01486   0.00632  -0.0632   0.5155   0.3411
   0.250   0.4387   0.01488   0.00639  -0.0628   0.5070   0.3608
   0.500   0.4652   0.01487   0.00636  -0.0623   0.4996   0.3792
   0.750   0.4915   0.01491   0.00639  -0.0619   0.4925   0.3973
   1.000   0.5176   0.01492   0.00644  -0.0614   0.4853   0.4157
   1.250   0.5443   0.01496   0.00643  -0.0610   0.4795   0.4349
   1.500   0.5700   0.01500   0.00655  -0.0605   0.4734   0.4558
   1.750   0.5957   0.01500   0.00663  -0.0600   0.4676   0.4817
   2.000   0.6207   0.01493   0.00667  -0.0594   0.4626   0.5196
   2.250   0.7324   0.01413   0.00699  -0.0757   0.4533   1.0000
   2.500   0.7571   0.01436   0.00711  -0.0750   0.4482   1.0000
   2.750   0.7823   0.01466   0.00723  -0.0744   0.4439   1.0000
   3.000   0.8066   0.01499   0.00749  -0.0737   0.4397   1.0000
   3.250   0.8303   0.01526   0.00775  -0.0729   0.4353   1.0000
   3.500   0.8545   0.01554   0.00797  -0.0722   0.4311   1.0000
   3.750   0.8792   0.01585   0.00817  -0.0715   0.4272   1.0000
   4.000   0.9046   0.01628   0.00847  -0.0710   0.4233   1.0000
   4.250   0.9268   0.01657   0.00881  -0.0701   0.4194   1.0000
   4.500   0.9502   0.01689   0.00914  -0.0693   0.4155   1.0000
   4.750   0.9743   0.01722   0.00942  -0.0686   0.4120   1.0000
   5.000   0.9993   0.01757   0.00969  -0.0681   0.4088   1.0000
   5.250   1.0256   0.01812   0.01012  -0.0678   0.4055   1.0000
   5.500   1.0462   0.01845   0.01055  -0.0667   0.4022   1.0000
   5.750   1.0680   0.01882   0.01096  -0.0657   0.3986   1.0000
   6.000   1.0911   0.01918   0.01132  -0.0649   0.3951   1.0000
   6.250   1.1154   0.01955   0.01165  -0.0643   0.3921   1.0000
   6.500   1.1412   0.01998   0.01201  -0.0640   0.3894   1.0000
   6.750   1.1656   0.02059   0.01260  -0.0636   0.3865   1.0000
   7.000   1.1844   0.02102   0.01315  -0.0623   0.3835   1.0000
   7.250   1.2046   0.02146   0.01365  -0.0612   0.3800   1.0000
   7.500   1.2267   0.02187   0.01410  -0.0603   0.3769   1.0000
   7.750   1.2506   0.02229   0.01450  -0.0598   0.3743   1.0000
   8.000   1.2764   0.02273   0.01489  -0.0596   0.3718   1.0000
   8.250   1.3027   0.02343   0.01554  -0.0595   0.3690   1.0000
   8.500   1.3181   0.02395   0.01622  -0.0578   0.3662   1.0000
   8.750   1.3348   0.02452   0.01690  -0.0564   0.3630   1.0000
   9.000   1.3537   0.02507   0.01753  -0.0553   0.3602   1.0000
   9.250   1.3753   0.02554   0.01803  -0.0545   0.3575   1.0000
   9.500   1.4002   0.02594   0.01840  -0.0542   0.3550   1.0000
   9.750   1.4288   0.02646   0.01885  -0.0545   0.3523   1.0000
  10.000   1.4438   0.02727   0.01978  -0.0530   0.3498   1.0000
  10.250   1.4540   0.02806   0.02074  -0.0509   0.3470   1.0000
  10.500   1.4661   0.02878   0.02157  -0.0491   0.3439   1.0000
  10.750   1.4820   0.02936   0.02222  -0.0477   0.3411   1.0000
  11.000   1.5044   0.02972   0.02258  -0.0471   0.3384   1.0000
  11.250   1.5362   0.02993   0.02270  -0.0477   0.3356   1.0000
  11.500   1.5462   0.03073   0.02361  -0.0457   0.3322   1.0000
  11.750   1.5412   0.03166   0.02473  -0.0418   0.3286   1.0000
  12.000   1.5414   0.03229   0.02543  -0.0384   0.3251   1.0000
  12.250   1.5590   0.03245   0.02559  -0.0372   0.3218   1.0000
  12.500   1.5992   0.03226   0.02529  -0.0387   0.3186   1.0000
  12.750   1.5980   0.03325   0.02639  -0.0355   0.3155   1.0000
  13.000   1.5739   0.03509   0.02844  -0.0308   0.3122   1.0000
  13.250   1.5657   0.03657   0.03004  -0.0282   0.3086   1.0000
  13.500   1.5826   0.03686   0.03032  -0.0273   0.3052   1.0000
  13.750   1.6304   0.03573   0.02904  -0.0285   0.3016   1.0000
  14.000   1.6087   0.03815   0.03166  -0.0253   0.2984   1.0000
  14.250   1.5758   0.04165   0.03539  -0.0225   0.2946   1.0000
  14.500   1.5698   0.04372   0.03755  -0.0212   0.2910   1.0000
  14.750   1.5976   0.04334   0.03714  -0.0209   0.2879   1.0000
  15.000   1.6492   0.04158   0.03524  -0.0215   0.2846   1.0000
  15.250   1.5780   0.04860   0.04262  -0.0188   0.2807   1.0000
  15.500   1.5256   0.05538   0.04963  -0.0180   0.2759   1.0000
  15.750   1.5618   0.05391   0.04813  -0.0175   0.2727   1.0000
  16.000   1.6213   0.05049   0.04456  -0.0173   0.2697   1.0000
  16.250   1.3550   0.08356   0.07824  -0.0223   0.2560   1.0000
  16.500   1.4540   0.07306   0.06768  -0.0191   0.2571   1.0000
  16.750   1.5451   0.06458   0.05908  -0.0171   0.2558   1.0000
  17.000   1.3344   0.09541   0.09027  -0.0251   0.2400   1.0000
  17.250   1.4079   0.08762   0.08247  -0.0223   0.2406   1.0000
  17.500   1.5029   0.07744   0.07219  -0.0191   0.2402   1.0000
  17.750   1.3216   0.10655   0.10156  -0.0283   0.2232   1.0000
  18.000   1.3824   0.10030   0.09531  -0.0259   0.2230   1.0000
  18.250   1.5123   0.08452   0.07937  -0.0205   0.2242   1.0000
  18.500   1.3917   0.10503   0.10013  -0.0274   0.2114   1.0000
  18.750   1.2380   0.13323   0.12846  -0.0387   0.1866   1.0000
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