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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 100,000
Max Cl/Cd: 53.3 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe532-il-100000.txt
Download as CSV file: xf-goe532-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2610   0.10154   0.09658  -0.0331   1.0000   0.1155
  -8.750  -0.2832   0.10076   0.09594  -0.0356   1.0000   0.1196
  -8.500  -0.3238   0.10110   0.09650  -0.0367   1.0000   0.1204
  -8.250  -0.2752   0.09449   0.08982  -0.0331   1.0000   0.1235
  -8.000  -0.2690   0.09235   0.08775  -0.0312   1.0000   0.1265
  -7.750  -0.2766   0.09089   0.08640  -0.0293   1.0000   0.1300
  -7.500  -0.3014   0.09045   0.08611  -0.0263   1.0000   0.1327
  -7.250  -0.3353   0.09069   0.08652  -0.0221   1.0000   0.1336
  -6.750  -0.3393   0.08535   0.08134  -0.0247   0.9936   0.1390
  -6.500  -0.3053   0.07870   0.07460  -0.0448   0.9767   0.1526
  -6.250  -0.2687   0.07642   0.07237  -0.0390   0.9726   0.1576
  -6.000  -0.2356   0.07097   0.06688  -0.0511   0.9588   0.1714
  -5.750  -0.1010   0.05043   0.04647  -0.0702   0.9172   0.2038
  -5.500  -0.0648   0.04690   0.04291  -0.0720   0.9089   0.2174
  -5.250  -0.0406   0.04344   0.03946  -0.0719   0.8949   0.2271
  -5.000  -0.0205   0.03991   0.03588  -0.0747   0.8791   0.2435
  -4.750  -0.0056   0.03641   0.03220  -0.0817   0.8598   0.2734
  -4.500   0.0007   0.03259   0.02605  -0.1043   0.8860   0.1162
  -4.250   0.0408   0.02892   0.02150  -0.1065   0.8738   0.1044
  -4.000   0.0732   0.02678   0.01904  -0.1070   0.8580   0.1023
  -3.750   0.1049   0.02522   0.01714  -0.1072   0.8418   0.1025
  -3.500   0.1355   0.02394   0.01554  -0.1069   0.8257   0.1032
  -3.250   0.1652   0.02279   0.01413  -0.1065   0.8101   0.1032
  -3.000   0.1945   0.02184   0.01296  -0.1060   0.7953   0.1039
  -2.750   0.2240   0.02103   0.01194  -0.1054   0.7817   0.1052
  -2.500   0.2501   0.02022   0.01111  -0.1045   0.7666   0.1086
  -2.250   0.2756   0.01966   0.01059  -0.1036   0.7522   0.1136
  -2.000   0.3022   0.01922   0.01009  -0.1028   0.7397   0.1187
  -1.750   0.3295   0.01866   0.00952  -0.1021   0.7295   0.1256
  -1.500   0.3543   0.01836   0.00926  -0.1013   0.7173   0.1385
  -1.250   0.3808   0.01779   0.00891  -0.1007   0.7077   0.1807
  -1.000   0.4005   0.01655   0.00914  -0.0989   0.6981   0.5594
  -0.750   0.4210   0.01640   0.00931  -0.0964   0.6889   0.6888
  -0.500   0.4417   0.01604   0.00926  -0.0936   0.6800   0.8113
  -0.250   0.4941   0.01585   0.00904  -0.0978   0.6692   1.0000
   0.000   0.5230   0.01606   0.00894  -0.0979   0.6607   1.0000
   0.250   0.5489   0.01639   0.00909  -0.0976   0.6512   1.0000
   0.500   0.5772   0.01661   0.00906  -0.0973   0.6430   1.0000
   0.750   0.6025   0.01697   0.00931  -0.0969   0.6341   1.0000
   1.000   0.6300   0.01726   0.00942  -0.0966   0.6268   1.0000
   1.250   0.6566   0.01764   0.00968  -0.0963   0.6200   1.0000
   1.500   0.6823   0.01799   0.00995  -0.0959   0.6120   1.0000
   1.750   0.7112   0.01826   0.01001  -0.0957   0.6056   1.0000
   2.000   0.7344   0.01869   0.01047  -0.0950   0.5969   1.0000
   2.250   0.7623   0.01895   0.01058  -0.0946   0.5899   1.0000
   2.500   0.7866   0.01933   0.01094  -0.0939   0.5812   1.0000
   2.750   0.8136   0.01954   0.01103  -0.0934   0.5729   1.0000
   3.000   0.8384   0.01988   0.01135  -0.0927   0.5646   1.0000
   3.250   0.8643   0.02019   0.01162  -0.0922   0.5570   1.0000
   3.500   0.8921   0.02050   0.01182  -0.0919   0.5510   1.0000
   3.750   0.9147   0.02094   0.01235  -0.0911   0.5426   1.0000
   4.000   0.9428   0.02115   0.01245  -0.0907   0.5359   1.0000
   4.250   0.9655   0.02159   0.01298  -0.0899   0.5274   1.0000
   4.500   0.9925   0.02179   0.01311  -0.0894   0.5196   1.0000
   4.750   1.0160   0.02215   0.01351  -0.0885   0.5106   1.0000
   5.000   1.0430   0.02223   0.01354  -0.0879   0.5015   1.0000
   5.250   1.0655   0.02250   0.01386  -0.0869   0.4902   1.0000
   5.500   1.0925   0.02250   0.01376  -0.0862   0.4798   1.0000
   5.750   1.1162   0.02255   0.01382  -0.0851   0.4671   1.0000
   6.000   1.1382   0.02269   0.01399  -0.0839   0.4534   1.0000
   6.250   1.1611   0.02277   0.01406  -0.0827   0.4392   1.0000
   6.500   1.1837   0.02283   0.01410  -0.0815   0.4240   1.0000
   6.750   1.2053   0.02294   0.01417  -0.0801   0.4078   1.0000
   7.000   1.2257   0.02312   0.01432  -0.0786   0.3910   1.0000
   7.250   1.2460   0.02340   0.01459  -0.0772   0.3750   1.0000
   7.500   1.2664   0.02376   0.01488  -0.0759   0.3606   1.0000
   7.750   1.2870   0.02415   0.01521  -0.0746   0.3478   1.0000
   8.000   1.3055   0.02472   0.01583  -0.0732   0.3355   1.0000
   8.250   1.3252   0.02530   0.01644  -0.0720   0.3253   1.0000
   8.500   1.3464   0.02579   0.01684  -0.0709   0.3167   1.0000
   8.750   1.3639   0.02648   0.01764  -0.0695   0.3072   1.0000
   9.000   1.3834   0.02704   0.01814  -0.0683   0.2989   1.0000
   9.250   1.3997   0.02771   0.01888  -0.0667   0.2899   1.0000
   9.500   1.4182   0.02841   0.01957  -0.0655   0.2824   1.0000
   9.750   1.4343   0.02916   0.02038  -0.0639   0.2744   1.0000
  10.000   1.4502   0.02996   0.02119  -0.0624   0.2664   1.0000
  10.250   1.4648   0.03076   0.02201  -0.0607   0.2580   1.0000
  10.500   1.4768   0.03173   0.02304  -0.0588   0.2495   1.0000
  10.750   1.4936   0.03263   0.02381  -0.0575   0.2401   1.0000
  11.000   1.4956   0.03376   0.02514  -0.0543   0.2314   1.0000
  11.250   1.5059   0.03496   0.02627  -0.0523   0.2212   1.0000
  11.500   1.5134   0.03622   0.02748  -0.0501   0.2104   1.0000
  11.750   1.5120   0.03788   0.02926  -0.0471   0.2004   1.0000
  12.000   1.5208   0.03954   0.03085  -0.0454   0.1900   1.0000
  12.250   1.5278   0.04117   0.03247  -0.0436   0.1810   1.0000
  12.500   1.5331   0.04317   0.03457  -0.0419   0.1737   1.0000
  12.750   1.5392   0.04493   0.03639  -0.0402   0.1674   1.0000
  13.000   1.5567   0.04664   0.03805  -0.0396   0.1614   1.0000
  13.250   1.5485   0.04902   0.04071  -0.0374   0.1576   1.0000
  13.500   1.5519   0.05100   0.04281  -0.0360   0.1534   1.0000
  13.750   1.5840   0.05217   0.04379  -0.0363   0.1485   1.0000
  14.000   1.5692   0.05516   0.04712  -0.0343   0.1465   1.0000
  14.250   1.5564   0.05841   0.05066  -0.0329   0.1441   1.0000
  14.500   1.5473   0.06162   0.05409  -0.0320   0.1417   1.0000
  14.750   1.5454   0.06438   0.05698  -0.0315   0.1391   1.0000
  15.000   1.5823   0.06457   0.05697  -0.0312   0.1353   1.0000
  15.250   1.5555   0.06944   0.06220  -0.0308   0.1343   1.0000
  15.500   1.5250   0.07528   0.06837  -0.0314   0.1334   1.0000
  15.750   1.4874   0.08256   0.07598  -0.0332   0.1328   1.0000
  16.000   1.4327   0.09294   0.08669  -0.0371   0.1327   1.0000
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