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GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 704 AIRFOIL (goe704-il)
Reynolds number: 100,000
Max Cl/Cd: 44.45 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe704-il-100000-n5.txt
Download as CSV file: xf-goe704-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 704 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8079   0.07022   0.06490  -0.0375   1.0000   0.0324
 -12.500  -0.8380   0.06002   0.05449  -0.0466   1.0000   0.0320
 -12.250  -0.8624   0.05393   0.04814  -0.0494   1.0000   0.0320
 -12.000  -0.8820   0.04954   0.04346  -0.0491   1.0000   0.0323
 -11.750  -0.8941   0.04639   0.04010  -0.0472   1.0000   0.0328
 -11.500  -0.8982   0.04431   0.03794  -0.0448   1.0000   0.0336
 -11.250  -0.8997   0.04238   0.03589  -0.0422   1.0000   0.0345
 -11.000  -0.8974   0.04039   0.03375  -0.0400   1.0000   0.0358
 -10.750  -0.8932   0.03833   0.03143  -0.0378   1.0000   0.0377
 -10.500  -0.8871   0.03614   0.02889  -0.0357   1.0000   0.0399
 -10.250  -0.8766   0.03481   0.02755  -0.0339   1.0000   0.0421
 -10.000  -0.8646   0.03334   0.02593  -0.0321   1.0000   0.0450
  -9.750  -0.8520   0.03164   0.02392  -0.0303   1.0000   0.0486
  -9.500  -0.8377   0.03064   0.02294  -0.0287   1.0000   0.0523
  -9.250  -0.8221   0.02942   0.02147  -0.0271   1.0000   0.0573
  -9.000  -0.8067   0.02856   0.02061  -0.0254   1.0000   0.0617
  -8.750  -0.7906   0.02776   0.01966  -0.0238   1.0000   0.0675
  -8.500  -0.7760   0.02720   0.01908  -0.0218   1.0000   0.0725
  -8.250  -0.7626   0.02674   0.01851  -0.0195   1.0000   0.0785
  -8.000  -0.7483   0.02641   0.01814  -0.0176   0.9986   0.0841
  -7.750  -0.7136   0.02579   0.01723  -0.0195   0.9896   0.0934
  -7.500  -0.6788   0.02542   0.01684  -0.0215   0.9811   0.1007
  -7.250  -0.6442   0.02468   0.01587  -0.0233   0.9730   0.1086
  -7.000  -0.6116   0.02423   0.01532  -0.0247   0.9633   0.1161
  -6.750  -0.5787   0.02359   0.01448  -0.0260   0.9544   0.1235
  -6.500  -0.5457   0.02313   0.01392  -0.0273   0.9460   0.1310
  -6.250  -0.5152   0.02257   0.01318  -0.0280   0.9362   0.1381
  -6.000  -0.4832   0.02210   0.01265  -0.0290   0.9286   0.1451
  -5.750  -0.4545   0.02166   0.01199  -0.0293   0.9185   0.1521
  -5.500  -0.4251   0.02117   0.01152  -0.0297   0.9106   0.1584
  -5.250  -0.3970   0.02079   0.01100  -0.0298   0.9016   0.1655
  -5.000  -0.3692   0.02034   0.01053  -0.0299   0.8937   0.1719
  -4.750  -0.3419   0.01998   0.01010  -0.0298   0.8854   0.1788
  -4.500  -0.3146   0.01960   0.00966  -0.0296   0.8781   0.1853
  -4.250  -0.2882   0.01926   0.00931  -0.0294   0.8702   0.1922
  -4.000  -0.2610   0.01894   0.00892  -0.0291   0.8635   0.1994
  -3.750  -0.2350   0.01861   0.00863  -0.0288   0.8558   0.2062
  -3.500  -0.2077   0.01833   0.00830  -0.0286   0.8500   0.2153
  -3.250  -0.1820   0.01808   0.00809  -0.0282   0.8421   0.2256
  -3.000  -0.1556   0.01781   0.00785  -0.0278   0.8360   0.2375
  -2.750  -0.1295   0.01758   0.00765  -0.0275   0.8291   0.2520
  -2.500  -0.1032   0.01734   0.00748  -0.0271   0.8224   0.2713
  -2.250  -0.0766   0.01709   0.00732  -0.0268   0.8166   0.2982
  -2.000  -0.0506   0.01685   0.00722  -0.0265   0.8091   0.3334
  -1.750  -0.0244   0.01653   0.00707  -0.0260   0.8032   0.3800
  -1.500   0.0001   0.01616   0.00699  -0.0254   0.7954   0.4452
  -1.250   0.0812   0.01546   0.00785  -0.0338   0.7899   0.8426
  -1.000   0.0995   0.01572   0.00800  -0.0311   0.7806   0.8937
  -0.750   0.1306   0.01597   0.00812  -0.0308   0.7714   0.9232
  -0.500   0.1677   0.01622   0.00827  -0.0321   0.7611   0.9453
  -0.250   0.2166   0.01636   0.00827  -0.0359   0.7528   0.9624
   0.000   0.2689   0.01644   0.00828  -0.0407   0.7430   0.9790
   0.250   0.3392   0.01632   0.00806  -0.0494   0.7334   1.0000
   0.500   0.3636   0.01629   0.00796  -0.0487   0.7240   1.0000
   0.750   0.3884   0.01628   0.00791  -0.0482   0.7134   1.0000
   1.000   0.4128   0.01626   0.00782  -0.0474   0.7033   1.0000
   1.250   0.4372   0.01623   0.00774  -0.0467   0.6919   1.0000
   1.500   0.4616   0.01622   0.00771  -0.0461   0.6791   1.0000
   1.750   0.4859   0.01620   0.00766  -0.0453   0.6656   1.0000
   2.000   0.5101   0.01618   0.00760  -0.0445   0.6513   1.0000
   2.250   0.5343   0.01617   0.00756  -0.0438   0.6360   1.0000
   2.500   0.5584   0.01616   0.00754  -0.0430   0.6195   1.0000
   2.750   0.5824   0.01617   0.00753  -0.0422   0.6020   1.0000
   3.000   0.6062   0.01619   0.00751  -0.0413   0.5833   1.0000
   3.250   0.6298   0.01624   0.00752  -0.0405   0.5627   1.0000
   3.500   0.6531   0.01632   0.00754  -0.0396   0.5398   1.0000
   3.750   0.6761   0.01644   0.00759  -0.0386   0.5162   1.0000
   4.000   0.6986   0.01662   0.00767  -0.0375   0.4910   1.0000
   4.250   0.7207   0.01686   0.00779  -0.0365   0.4658   1.0000
   4.500   0.7422   0.01716   0.00796  -0.0354   0.4420   1.0000
   4.750   0.7635   0.01749   0.00821  -0.0343   0.4193   1.0000
   5.000   0.7843   0.01786   0.00849  -0.0331   0.3986   1.0000
   5.250   0.8048   0.01826   0.00880  -0.0319   0.3803   1.0000
   5.500   0.8251   0.01867   0.00915  -0.0307   0.3638   1.0000
   5.750   0.8452   0.01908   0.00952  -0.0294   0.3489   1.0000
   6.000   0.8652   0.01949   0.00992  -0.0282   0.3353   1.0000
   6.250   0.8849   0.01991   0.01033  -0.0269   0.3232   1.0000
   6.500   0.9042   0.02036   0.01078  -0.0255   0.3127   1.0000
   6.750   0.9232   0.02081   0.01123  -0.0241   0.3024   1.0000
   7.000   0.9421   0.02124   0.01171  -0.0227   0.2922   1.0000
   7.250   0.9601   0.02172   0.01217  -0.0211   0.2831   1.0000
   7.500   0.9781   0.02217   0.01270  -0.0196   0.2734   1.0000
   7.750   0.9956   0.02265   0.01322  -0.0179   0.2648   1.0000
   8.000   1.0125   0.02314   0.01375  -0.0162   0.2568   1.0000
   8.250   1.0296   0.02364   0.01432  -0.0146   0.2493   1.0000
   8.500   1.0459   0.02415   0.01490  -0.0128   0.2423   1.0000
   8.750   1.0623   0.02469   0.01553  -0.0110   0.2359   1.0000
   9.000   1.0780   0.02523   0.01617  -0.0092   0.2291   1.0000
   9.250   1.0929   0.02582   0.01680  -0.0072   0.2231   1.0000
   9.500   1.1067   0.02639   0.01751  -0.0051   0.2153   1.0000
   9.750   1.1183   0.02699   0.01815  -0.0028   0.2073   1.0000
  10.000   1.1276   0.02759   0.01884  -0.0002   0.1976   1.0000
  10.250   1.1356   0.02823   0.01960   0.0026   0.1868   1.0000
  10.500   1.1409   0.02895   0.02034   0.0056   0.1768   1.0000
  10.750   1.1438   0.02973   0.02117   0.0089   0.1669   1.0000
  11.000   1.1491   0.03059   0.02214   0.0115   0.1559   1.0000
  11.250   1.1543   0.03160   0.02323   0.0138   0.1452   1.0000
  11.500   1.1594   0.03276   0.02446   0.0158   0.1331   1.0000
  11.750   1.1638   0.03411   0.02585   0.0175   0.1184   1.0000
  12.000   1.1653   0.03578   0.02753   0.0191   0.1040   1.0000
  12.250   1.1645   0.03781   0.02953   0.0205   0.0931   1.0000
  12.500   1.1618   0.04018   0.03189   0.0217   0.0838   1.0000
  12.750   1.1557   0.04300   0.03472   0.0227   0.0752   1.0000
  13.250   1.1486   0.04872   0.04067   0.0237   0.0517   1.0000
  13.500   1.1392   0.05241   0.04438   0.0237   0.0448   1.0000
  13.750   1.1282   0.05649   0.04853   0.0233   0.0410   1.0000
  14.000   1.1155   0.06100   0.05314   0.0225   0.0386   1.0000
  14.250   1.1006   0.06611   0.05835   0.0211   0.0371   1.0000
  14.500   1.0852   0.07163   0.06399   0.0193   0.0361   1.0000
  14.750   1.0704   0.07740   0.06992   0.0172   0.0352   1.0000
  15.000   1.0554   0.08342   0.07609   0.0148   0.0343   1.0000
  15.250   1.0411   0.08952   0.08233   0.0124   0.0336   1.0000
  15.500   1.0276   0.09558   0.08851   0.0099   0.0328   1.0000
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