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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 200,000
Max Cl/Cd: 82 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe371-il-200000.txt
Download as CSV file: xf-goe371-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 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  -0.3280   0.08907   0.08574  -0.0269   1.0000   0.0298
  -7.250  -0.3336   0.08724   0.08399  -0.0251   1.0000   0.0303
  -7.000  -0.3398   0.08540   0.08222  -0.0236   1.0000   0.0308
  -6.750  -0.3461   0.08362   0.08052  -0.0222   1.0000   0.0311
  -6.500  -0.3549   0.08206   0.07903  -0.0205   1.0000   0.0315
  -6.250  -0.3651   0.08060   0.07764  -0.0187   1.0000   0.0322
  -6.000  -0.3498   0.07712   0.07415  -0.0234   0.9971   0.0334
  -5.750  -0.2790   0.07104   0.06783  -0.0474   0.9885   0.0367
  -5.500  -0.2554   0.06387   0.06064  -0.0525   0.9842   0.0378
  -5.250  -0.2341   0.06039   0.05717  -0.0539   0.9785   0.0392
  -5.000  -0.2003   0.05645   0.05314  -0.0594   0.9733   0.0417
  -4.750  -0.1342   0.05153   0.04772  -0.0737   0.9675   0.0482
  -4.500  -0.1133   0.04580   0.04203  -0.0766   0.9613   0.0501
  -4.250  -0.0818   0.04331   0.03953  -0.0795   0.9578   0.0550
  -4.000  -0.0380   0.03859   0.03437  -0.0859   0.9516   0.0629
  -3.750  -0.0078   0.03619   0.03199  -0.0880   0.9464   0.0673
  -3.500   0.0362   0.03265   0.02808  -0.0930   0.9432   0.0780
  -3.250   0.0706   0.03046   0.02560  -0.0953   0.9373   0.0913
  -3.000   0.1046   0.02868   0.02354  -0.0972   0.9317   0.1051
  -2.750   0.1404   0.02662   0.02130  -0.0995   0.9281   0.1196
  -2.500   0.1662   0.02473   0.01946  -0.0998   0.9206   0.1281
  -2.250   0.1977   0.02306   0.01765  -0.1011   0.9154   0.1520
  -2.000   0.2410   0.02024   0.01367  -0.1007   0.9101   0.0896
  -1.750   0.2708   0.01722   0.01035  -0.1003   0.9031   0.0696
  -1.500   0.3050   0.01585   0.00870  -0.1008   0.8983   0.0673
  -1.250   0.3313   0.01502   0.00771  -0.1000   0.8890   0.0670
  -1.000   0.3625   0.01410   0.00664  -0.1000   0.8827   0.0654
  -0.750   0.3889   0.01347   0.00597  -0.0993   0.8735   0.0653
  -0.500   0.4166   0.01292   0.00540  -0.0988   0.8653   0.0662
  -0.250   0.4443   0.01245   0.00492  -0.0983   0.8565   0.0680
   0.000   0.4700   0.01215   0.00462  -0.0975   0.8460   0.0715
   0.250   0.4968   0.01186   0.00431  -0.0968   0.8359   0.0760
   0.500   0.5243   0.01158   0.00400  -0.0963   0.8262   0.0826
   0.750   0.5499   0.01134   0.00382  -0.0954   0.8140   0.1065
   1.000   0.5930   0.00922   0.00372  -0.0987   0.8022   1.0000
   1.250   0.6186   0.00927   0.00362  -0.0977   0.7874   1.0000
   1.500   0.6439   0.00932   0.00352  -0.0967   0.7707   1.0000
   1.750   0.6690   0.00939   0.00344  -0.0956   0.7524   1.0000
   2.000   0.6932   0.00947   0.00342  -0.0945   0.7312   1.0000
   2.250   0.7181   0.00957   0.00340  -0.0935   0.7106   1.0000
   2.500   0.7422   0.00967   0.00341  -0.0924   0.6864   1.0000
   2.750   0.7666   0.00979   0.00342  -0.0914   0.6621   1.0000
   3.000   0.7910   0.00993   0.00346  -0.0905   0.6378   1.0000
   3.250   0.8155   0.01009   0.00355  -0.0896   0.6135   1.0000
   3.500   0.8399   0.01030   0.00363  -0.0887   0.5918   1.0000
   3.750   0.8644   0.01055   0.00378  -0.0879   0.5724   1.0000
   4.000   0.8889   0.01084   0.00397  -0.0872   0.5552   1.0000
   4.250   0.9134   0.01115   0.00422  -0.0864   0.5388   1.0000
   4.500   0.9378   0.01149   0.00448  -0.0857   0.5234   1.0000
   4.750   0.9623   0.01182   0.00477  -0.0850   0.5087   1.0000
   5.000   0.9864   0.01216   0.00508  -0.0843   0.4931   1.0000
   5.250   1.0099   0.01246   0.00541  -0.0834   0.4746   1.0000
   5.500   1.0329   0.01276   0.00571  -0.0824   0.4543   1.0000
   5.750   1.0555   0.01309   0.00601  -0.0814   0.4336   1.0000
   6.000   1.0778   0.01337   0.00632  -0.0803   0.4093   1.0000
   6.250   1.0994   0.01368   0.00666  -0.0791   0.3810   1.0000
   6.500   1.1196   0.01406   0.00697  -0.0778   0.3403   1.0000
   6.750   1.1375   0.01467   0.00735  -0.0761   0.2911   1.0000
   7.000   1.1554   0.01541   0.00790  -0.0746   0.2543   1.0000
   7.250   1.1737   0.01616   0.00853  -0.0732   0.2278   1.0000
   7.500   1.1919   0.01693   0.00922  -0.0718   0.2058   1.0000
   7.750   1.2115   0.01757   0.00986  -0.0706   0.1845   1.0000
   8.000   1.2301   0.01826   0.01051  -0.0693   0.1616   1.0000
   8.250   1.2488   0.01894   0.01116  -0.0680   0.1300   1.0000
   8.500   1.2568   0.02068   0.01237  -0.0653   0.0648   1.0000
   8.750   1.2641   0.02249   0.01403  -0.0623   0.0423   1.0000
   9.000   1.2738   0.02389   0.01552  -0.0596   0.0365   1.0000
   9.250   1.2847   0.02508   0.01682  -0.0571   0.0330   1.0000
   9.500   1.2876   0.02665   0.01842  -0.0536   0.0303   1.0000
   9.750   1.2930   0.02810   0.01997  -0.0505   0.0288   1.0000
  10.000   1.3012   0.02938   0.02138  -0.0479   0.0271   1.0000
  10.250   1.3077   0.03094   0.02304  -0.0453   0.0260   1.0000
  10.500   1.3145   0.03262   0.02481  -0.0429   0.0251   1.0000
  10.750   1.3217   0.03444   0.02674  -0.0408   0.0242   1.0000
  11.000   1.3304   0.03651   0.02889  -0.0389   0.0236   1.0000
  11.250   1.3420   0.03897   0.03147  -0.0373   0.0230   1.0000
  11.500   1.3582   0.04284   0.03554  -0.0364   0.0223   1.0000
  11.750   1.3611   0.04509   0.03805  -0.0343   0.0218   1.0000
  12.000   1.3632   0.04750   0.04072  -0.0323   0.0215   1.0000
  12.250   1.3618   0.05014   0.04363  -0.0304   0.0211   1.0000
  12.500   1.3584   0.05338   0.04714  -0.0287   0.0210   1.0000
  12.750   1.3518   0.05702   0.05106  -0.0274   0.0210   1.0000
  13.000   1.3414   0.06102   0.05534  -0.0264   0.0210   1.0000
  13.250   1.3290   0.06537   0.05995  -0.0260   0.0211   1.0000
  13.500   1.3140   0.07016   0.06499  -0.0262   0.0211   1.0000
  13.750   1.2972   0.07544   0.07051  -0.0272   0.0212   1.0000
  14.000   1.2792   0.08116   0.07645  -0.0289   0.0214   1.0000
  14.250   1.2598   0.08753   0.08303  -0.0314   0.0215   1.0000
  14.500   1.2403   0.09435   0.09004  -0.0347   0.0217   1.0000
  14.750   1.2193   0.10190   0.09778  -0.0389   0.0218   1.0000
  15.000   1.1988   0.11003   0.10607  -0.0434   0.0220   1.0000
  15.250   1.1782   0.11880   0.11499  -0.0484   0.0222   1.0000
  15.500   1.1655   0.12608   0.12241  -0.0534   0.0224   1.0000
  15.750   1.1483   0.13518   0.13165  -0.0600   0.0226   1.0000
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