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GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 704 AIRFOIL (goe704-il)
Reynolds number: 50,000
Max Cl/Cd: 25.96 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe704-il-50000.txt
Download as CSV file: xf-goe704-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4635   0.11570   0.10860   0.0005   1.0000   0.3029
  -9.750  -0.4840   0.11428   0.10728  -0.0007   1.0000   0.3147
  -9.500  -0.4743   0.11039   0.10339  -0.0002   1.0000   0.3308
  -9.250  -0.4620   0.10630   0.09929   0.0004   1.0000   0.3464
  -9.000  -0.4612   0.10315   0.09617   0.0008   1.0000   0.3633
  -8.750  -0.4633   0.10016   0.09324   0.0013   1.0000   0.3803
  -8.250  -0.5940   0.07553   0.06875  -0.0248   1.0000   0.2183
  -8.000  -0.5889   0.07066   0.06386  -0.0245   1.0000   0.2166
  -7.750  -0.5951   0.06594   0.05907  -0.0237   1.0000   0.2150
  -7.500  -0.6047   0.06148   0.05449  -0.0222   1.0000   0.2133
  -7.250  -0.6163   0.05755   0.05039  -0.0195   1.0000   0.2127
  -7.000  -0.6278   0.05419   0.04681  -0.0160   1.0000   0.2142
  -6.750  -0.6390   0.05105   0.04332  -0.0122   1.0000   0.2166
  -6.500  -0.6405   0.04844   0.04052  -0.0089   1.0000   0.2209
  -6.250  -0.6343   0.04668   0.03867  -0.0061   1.0000   0.2277
  -6.000  -0.6360   0.04398   0.03541  -0.0030   1.0000   0.2335
  -5.750  -0.6241   0.04238   0.03385  -0.0008   1.0000   0.2412
  -5.500  -0.6174   0.04025   0.03119   0.0015   1.0000   0.2495
  -5.250  -0.6030   0.03887   0.02983   0.0033   1.0000   0.2585
  -5.000  -0.5903   0.03708   0.02760   0.0050   1.0000   0.2674
  -4.750  -0.5740   0.03592   0.02637   0.0064   1.0000   0.2777
  -4.500  -0.5570   0.03457   0.02479   0.0076   1.0000   0.2870
  -4.250  -0.5393   0.03351   0.02337   0.0087   1.0000   0.2982
  -4.000  -0.5195   0.03249   0.02236   0.0095   1.0000   0.3081
  -3.750  -0.4990   0.03157   0.02123   0.0102   1.0000   0.3193
  -3.500  -0.4778   0.03082   0.02021   0.0107   1.0000   0.3311
  -3.250  -0.4562   0.03004   0.01943   0.0112   1.0000   0.3420
  -3.000  -0.4345   0.02939   0.01871   0.0117   1.0000   0.3552
  -2.750  -0.4118   0.02882   0.01803   0.0120   1.0000   0.3692
  -2.500  -0.3874   0.02833   0.01749   0.0120   1.0000   0.3849
  -2.250  -0.3623   0.02792   0.01711   0.0119   1.0000   0.4062
  -2.000  -0.3367   0.02753   0.01677   0.0117   1.0000   0.4330
  -1.750  -0.1436   0.02664   0.01811  -0.0152   1.0000   1.0000
  -1.500  -0.1334   0.02696   0.01807  -0.0134   1.0000   1.0000
  -1.250  -0.1238   0.02731   0.01817  -0.0114   1.0000   1.0000
  -1.000  -0.1141   0.02768   0.01833  -0.0094   1.0000   1.0000
  -0.750  -0.1042   0.02809   0.01855  -0.0076   1.0000   1.0000
  -0.500  -0.0943   0.02853   0.01883  -0.0058   1.0000   1.0000
  -0.250  -0.0414   0.02939   0.01947  -0.0122   0.9870   1.0000
   0.000   0.0117   0.03025   0.02015  -0.0184   0.9725   1.0000
   0.250   0.0632   0.03106   0.02083  -0.0242   0.9572   1.0000
   0.500   0.1134   0.03181   0.02147  -0.0295   0.9412   1.0000
   0.750   0.1633   0.03249   0.02208  -0.0345   0.9249   1.0000
   1.000   0.2135   0.03310   0.02264  -0.0394   0.9081   1.0000
   1.250   0.2557   0.03365   0.02316  -0.0426   0.8903   1.0000
   1.500   0.2946   0.03416   0.02367  -0.0450   0.8713   1.0000
   1.750   0.3387   0.03457   0.02410  -0.0481   0.8519   1.0000
   2.000   0.3928   0.03475   0.02432  -0.0526   0.8325   1.0000
   2.250   0.4480   0.03463   0.02426  -0.0565   0.8134   1.0000
   2.500   0.4958   0.03437   0.02406  -0.0586   0.7941   1.0000
   2.750   0.5167   0.03471   0.02444  -0.0569   0.7709   1.0000
   3.000   0.5538   0.03439   0.02417  -0.0568   0.7506   1.0000
   3.250   0.5909   0.03385   0.02368  -0.0562   0.7314   1.0000
   3.500   0.6117   0.03397   0.02384  -0.0539   0.7090   1.0000
   3.750   0.6363   0.03381   0.02372  -0.0518   0.6877   1.0000
   4.000   0.6655   0.03330   0.02325  -0.0500   0.6684   1.0000
   4.250   0.6944   0.03273   0.02268  -0.0480   0.6500   1.0000
   4.500   0.7086   0.03322   0.02322  -0.0453   0.6269   1.0000
   4.750   0.7331   0.03297   0.02300  -0.0432   0.6078   1.0000
   5.000   0.7587   0.03266   0.02270  -0.0413   0.5898   1.0000
   5.250   0.7848   0.03236   0.02238  -0.0394   0.5725   1.0000
   5.500   0.8067   0.03249   0.02254  -0.0375   0.5547   1.0000
   5.750   0.8258   0.03300   0.02310  -0.0356   0.5374   1.0000
   6.000   0.8468   0.03346   0.02358  -0.0339   0.5216   1.0000
   6.250   0.8683   0.03392   0.02408  -0.0322   0.5065   1.0000
   6.500   0.8911   0.03436   0.02453  -0.0308   0.4924   1.0000
   6.750   0.9120   0.03513   0.02534  -0.0293   0.4794   1.0000
   7.000   0.9239   0.03664   0.02699  -0.0273   0.4664   1.0000
   7.250   0.9375   0.03797   0.02844  -0.0254   0.4537   1.0000
   7.500   0.9542   0.03900   0.02954  -0.0236   0.4411   1.0000
   7.750   0.9750   0.03963   0.03020  -0.0219   0.4278   1.0000
   8.000   0.9965   0.04009   0.03067  -0.0202   0.4133   1.0000
   8.250   1.0193   0.04055   0.03114  -0.0187   0.3991   1.0000
   8.500   1.0300   0.04204   0.03279  -0.0165   0.3871   1.0000
   8.750   1.0295   0.04441   0.03537  -0.0135   0.3768   1.0000
   9.000   1.0482   0.04563   0.03667  -0.0120   0.3661   1.0000
   9.250   1.0634   0.04710   0.03824  -0.0103   0.3552   1.0000
   9.500   1.0415   0.05104   0.04245  -0.0061   0.3475   1.0000
   9.750   1.0656   0.05194   0.04343  -0.0049   0.3354   1.0000
  10.000   1.0069   0.05861   0.05029   0.0004   0.3316   1.0000
  10.250   1.0335   0.05924   0.05103   0.0017   0.3192   1.0000
  10.500   0.9300   0.07076   0.06245   0.0053   0.3210   1.0000
  11.000   0.7531   0.10353   0.09477  -0.0069   0.3231   1.0000
  11.250   0.7319   0.11083   0.10204  -0.0093   0.3234   1.0000
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