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GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 100,000
Max Cl/Cd: 47.35 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe481a-il-100000.txt
Download as CSV file: xf-goe481a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.250  -0.2568   0.10746   0.10276  -0.0334   0.9704   0.1403
  -6.000  -0.2888   0.10589   0.10120  -0.0400   0.9521   0.1441
  -5.750  -0.2791   0.10111   0.09641  -0.0455   0.9416   0.1456
  -5.500  -0.2468   0.09757   0.09289  -0.0448   0.9348   0.1471
  -5.250  -0.2248   0.09449   0.08980  -0.0462   0.9256   0.1495
  -5.000  -0.2026   0.09080   0.08608  -0.0513   0.9175   0.1539
  -4.750  -0.2029   0.08537   0.08046  -0.0631   0.9018   0.1595
  -4.500  -0.1881   0.08254   0.07769  -0.0608   0.8902   0.1606
  -4.250  -0.1529   0.07940   0.07457  -0.0623   0.8861   0.1642
  -4.000  -0.1411   0.07635   0.07140  -0.0662   0.8716   0.1719
  -3.750  -0.1314   0.07228   0.06720  -0.0689   0.8585   0.1757
  -3.500  -0.0989   0.06907   0.06402  -0.0700   0.8536   0.1785
  -3.250  -0.0851   0.06686   0.06179  -0.0696   0.8410   0.1826
  -3.000  -0.0517   0.06239   0.05705  -0.0759   0.8353   0.1930
  -2.750  -0.0400   0.06047   0.05517  -0.0738   0.8222   0.1955
  -2.500  -0.0035   0.05712   0.05155  -0.0783   0.8175   0.2106
  -2.250   0.0081   0.05534   0.04986  -0.0758   0.8047   0.2138
  -2.000   0.0442   0.05239   0.04672  -0.0787   0.8001   0.2307
  -1.750   0.0623   0.04313   0.03583  -0.0804   0.7886   0.1452
  -1.500   0.0976   0.04037   0.03274  -0.0814   0.7835   0.1443
  -1.250   0.1382   0.03741   0.02935  -0.0828   0.7807   0.1445
  -0.750   0.1940   0.03380   0.02550  -0.0820   0.7644   0.1476
  -0.500   0.2427   0.03167   0.02320  -0.0847   0.7619   0.1527
  -0.250   0.2582   0.03112   0.02236  -0.0820   0.7491   0.1567
   0.000   0.3072   0.02895   0.02001  -0.0848   0.7454   0.1625
   0.250   0.3669   0.02707   0.01781  -0.0893   0.7424   0.1741
   0.500   0.3835   0.02658   0.01741  -0.0872   0.7295   0.1813
   0.750   0.4469   0.02470   0.01541  -0.0928   0.7247   0.1991
   1.000   0.4738   0.02423   0.01488  -0.0922   0.7133   0.2128
   1.250   0.5353   0.02298   0.01361  -0.0980   0.7057   0.2348
   1.500   0.5632   0.02280   0.01337  -0.0977   0.6943   0.2496
   1.750   0.6283   0.02195   0.01254  -0.1046   0.6850   0.2736
   2.000   0.6459   0.02207   0.01266  -0.1023   0.6728   0.2864
   2.250   0.7248   0.02145   0.01204  -0.1121   0.6632   0.3119
   2.500   0.7307   0.02171   0.01240  -0.1077   0.6511   0.3238
   2.750   0.7916   0.02145   0.01223  -0.1141   0.6409   0.3635
   3.000   0.9565   0.02063   0.01254  -0.1420   0.6236   1.0000
   3.250   0.9617   0.02115   0.01302  -0.1374   0.6130   1.0000
   3.500   1.0046   0.02143   0.01302  -0.1401   0.6030   1.0000
   3.750   1.0062   0.02195   0.01355  -0.1348   0.5924   1.0000
   4.000   1.0500   0.02220   0.01351  -0.1376   0.5819   1.0000
   4.250   1.0473   0.02273   0.01410  -0.1315   0.5718   1.0000
   4.500   1.0885   0.02299   0.01411  -0.1339   0.5620   1.0000
   4.750   1.0868   0.02352   0.01472  -0.1280   0.5524   1.0000
   5.000   1.1205   0.02378   0.01480  -0.1289   0.5430   1.0000
   5.250   1.1257   0.02431   0.01535  -0.1244   0.5338   1.0000
   5.500   1.1494   0.02461   0.01556  -0.1234   0.5248   1.0000
   5.750   1.1668   0.02508   0.01598  -0.1213   0.5164   1.0000
   6.000   1.1777   0.02553   0.01643  -0.1179   0.5079   1.0000
   6.250   1.2175   0.02584   0.01656  -0.1201   0.5002   1.0000
   6.500   1.2120   0.02646   0.01732  -0.1137   0.4924   1.0000
   6.750   1.2359   0.02680   0.01758  -0.1128   0.4847   1.0000
   7.000   1.2567   0.02730   0.01805  -0.1115   0.4775   1.0000
   7.250   1.2590   0.02789   0.01873  -0.1066   0.4699   1.0000
   7.500   1.2948   0.02812   0.01881  -0.1080   0.4626   1.0000
   7.750   1.2947   0.02880   0.01959  -0.1028   0.4555   1.0000
   8.000   1.3029   0.02923   0.02005  -0.0991   0.4479   1.0000
   8.250   1.3405   0.02949   0.02017  -0.1008   0.4401   1.0000
   8.500   1.3264   0.03016   0.02100  -0.0931   0.4327   1.0000
   8.750   1.3548   0.03033   0.02106  -0.0930   0.4247   1.0000
   9.000   1.3579   0.03096   0.02176  -0.0886   0.4171   1.0000
   9.250   1.3646   0.03145   0.02229  -0.0849   0.4090   1.0000
   9.500   1.3939   0.03173   0.02245  -0.0851   0.4009   1.0000
   9.750   1.3841   0.03255   0.02343  -0.0787   0.3928   1.0000
  10.000   1.4251   0.03252   0.02318  -0.0807   0.3836   1.0000
  10.250   1.4050   0.03357   0.02445  -0.0729   0.3755   1.0000
  10.500   1.4466   0.03342   0.02402  -0.0749   0.3654   1.0000
  10.750   1.4234   0.03465   0.02551  -0.0669   0.3574   1.0000
  11.000   1.4607   0.03450   0.02508  -0.0682   0.3472   1.0000
  11.250   1.4389   0.03589   0.02673  -0.0608   0.3395   1.0000
  11.500   1.4653   0.03602   0.02669  -0.0605   0.3303   1.0000
  11.750   1.4552   0.03736   0.02818  -0.0553   0.3227   1.0000
  12.000   1.4671   0.03793   0.02870  -0.0531   0.3145   1.0000
  12.250   1.4751   0.03888   0.02965  -0.0506   0.3073   1.0000
  12.500   1.4695   0.04026   0.03117  -0.0466   0.3004   1.0000
  12.750   1.5088   0.04022   0.03087  -0.0480   0.2928   1.0000
  13.000   1.4846   0.04241   0.03336  -0.0420   0.2877   1.0000
  13.250   1.4849   0.04371   0.03474  -0.0391   0.2815   1.0000
  13.500   1.5185   0.04377   0.03461  -0.0397   0.2749   1.0000
  13.750   1.4927   0.04638   0.03752  -0.0345   0.2703   1.0000
  14.000   1.4898   0.04805   0.03928  -0.0317   0.2647   1.0000
  14.250   1.5285   0.04766   0.03866  -0.0326   0.2581   1.0000
  14.500   1.4969   0.05100   0.04232  -0.0278   0.2541   1.0000
  14.750   1.4839   0.05352   0.04501  -0.0249   0.2491   1.0000
  15.000   1.5340   0.05214   0.04331  -0.0262   0.2419   1.0000
  15.250   1.4942   0.05651   0.04805  -0.0219   0.2384   1.0000
  15.500   1.4677   0.06048   0.05223  -0.0194   0.2338   1.0000
  15.750   1.5297   0.05768   0.04905  -0.0204   0.2259   1.0000
  16.000   1.4802   0.06353   0.05530  -0.0172   0.2227   1.0000
  16.250   1.4392   0.06959   0.06165  -0.0156   0.2185   1.0000
  16.500   1.5189   0.06454   0.05614  -0.0158   0.2102   1.0000
  16.750   1.4568   0.07252   0.06454  -0.0141   0.2074   1.0000
  17.000   1.3579   0.08657   0.07908  -0.0153   0.2042   1.0000
  17.250   1.4547   0.07754   0.06965  -0.0128   0.1969   1.0000
  17.500   1.4234   0.08380   0.07609  -0.0130   0.1931   1.0000
  17.750   0.8715   0.19990   0.19306  -0.0651   0.2253   1.0000
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