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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 500,000
Max Cl/Cd: 108.58 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe371-il-500000.txt
Download as CSV file: xf-goe371-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2556   0.08632   0.08423  -0.0306   1.0000   0.0168
  -8.500  -0.2537   0.08352   0.08146  -0.0301   1.0000   0.0170
  -8.250  -0.3397   0.09319   0.09101  -0.0301   1.0000   0.0164
  -8.000  -0.3317   0.09002   0.08786  -0.0280   1.0000   0.0167
  -7.750  -0.3336   0.08794   0.08582  -0.0270   1.0000   0.0168
  -7.500  -0.3390   0.08623   0.08416  -0.0249   1.0000   0.0170
  -7.250  -0.3518   0.08512   0.08310  -0.0215   1.0000   0.0171
  -7.000  -0.3324   0.08117   0.07916  -0.0266   0.9971   0.0175
  -6.750  -0.3052   0.07668   0.07466  -0.0341   0.9927   0.0181
  -6.500  -0.2767   0.07197   0.06992  -0.0421   0.9874   0.0189
  -6.250  -0.2271   0.06511   0.06297  -0.0593   0.9816   0.0209
  -6.000  -0.1897   0.05940   0.05718  -0.0690   0.9751   0.0211
  -5.750  -0.1497   0.05334   0.05100  -0.0782   0.9714   0.0212
  -5.500  -0.1291   0.04773   0.04535  -0.0827   0.9646   0.0219
  -5.250  -0.1011   0.04538   0.04295  -0.0856   0.9587   0.0230
  -2.750   0.1763   0.01730   0.01227  -0.0988   0.8472   0.0498
  -2.500   0.2011   0.01607   0.01102  -0.0986   0.8385   0.0527
  -2.250   0.2278   0.01575   0.01054  -0.0982   0.8297   0.0590
  -2.000   0.2530   0.01457   0.00923  -0.0980   0.8216   0.0665
  -1.750   0.2790   0.01405   0.00855  -0.0977   0.8134   0.0787
  -1.500   0.3088   0.01124   0.00518  -0.0960   0.8059   0.0442
  -1.250   0.3355   0.01047   0.00426  -0.0954   0.7979   0.0426
  -1.000   0.3621   0.00995   0.00367  -0.0949   0.7896   0.0423
  -0.750   0.3886   0.00959   0.00324  -0.0944   0.7821   0.0430
  -0.500   0.4150   0.00920   0.00281  -0.0939   0.7735   0.0427
  -0.250   0.4414   0.00892   0.00248  -0.0934   0.7654   0.0430
   0.000   0.4676   0.00871   0.00222  -0.0928   0.7556   0.0438
   0.250   0.4939   0.00854   0.00202  -0.0923   0.7440   0.0449
   0.500   0.5200   0.00843   0.00186  -0.0918   0.7310   0.0459
   0.750   0.5462   0.00836   0.00173  -0.0912   0.7172   0.0471
   1.000   0.5723   0.00831   0.00162  -0.0907   0.7020   0.0493
   1.250   0.5984   0.00827   0.00154  -0.0901   0.6851   0.0541
   1.500   0.6236   0.00809   0.00154  -0.0895   0.6653   0.1416
   1.750   0.6642   0.00634   0.00166  -0.0929   0.6327   1.0000
   2.000   0.6874   0.00657   0.00165  -0.0917   0.5873   1.0000
   2.250   0.7103   0.00688   0.00173  -0.0907   0.5502   1.0000
   2.500   0.7347   0.00713   0.00183  -0.0899   0.5276   1.0000
   2.750   0.7596   0.00736   0.00195  -0.0893   0.5112   1.0000
   3.000   0.7848   0.00757   0.00208  -0.0887   0.4975   1.0000
   3.250   0.8101   0.00776   0.00223  -0.0882   0.4850   1.0000
   3.500   0.8355   0.00796   0.00237  -0.0877   0.4738   1.0000
   3.750   0.8608   0.00816   0.00252  -0.0871   0.4635   1.0000
   4.000   0.8863   0.00834   0.00267  -0.0866   0.4510   1.0000
   4.250   0.9117   0.00851   0.00284  -0.0861   0.4389   1.0000
   4.500   0.9371   0.00869   0.00300  -0.0856   0.4269   1.0000
   4.750   0.9622   0.00888   0.00317  -0.0851   0.4119   1.0000
   5.000   0.9870   0.00909   0.00334  -0.0845   0.3950   1.0000
   5.250   1.0115   0.00932   0.00354  -0.0839   0.3755   1.0000
   5.500   1.0350   0.00962   0.00373  -0.0831   0.3384   1.0000
   5.750   1.0560   0.01017   0.00401  -0.0820   0.2820   1.0000
   6.000   1.0762   0.01083   0.00442  -0.0808   0.2369   1.0000
   6.250   1.0978   0.01138   0.00484  -0.0799   0.2095   1.0000
   6.500   1.1201   0.01184   0.00523  -0.0790   0.1915   1.0000
   6.750   1.1428   0.01226   0.00560  -0.0782   0.1745   1.0000
   7.000   1.1655   0.01267   0.00598  -0.0774   0.1579   1.0000
   7.250   1.1871   0.01317   0.00638  -0.0765   0.1363   1.0000
   7.500   1.2077   0.01377   0.00684  -0.0754   0.1030   1.0000
   7.750   1.2233   0.01485   0.00761  -0.0736   0.0591   1.0000
   8.000   1.2378   0.01604   0.00855  -0.0716   0.0260   1.0000
   8.250   1.2563   0.01680   0.00933  -0.0701   0.0203   1.0000
   8.500   1.2740   0.01762   0.01020  -0.0685   0.0177   1.0000
   8.750   1.2891   0.01865   0.01136  -0.0664   0.0162   1.0000
   9.000   1.3061   0.01940   0.01222  -0.0648   0.0155   1.0000
   9.250   1.3211   0.02029   0.01321  -0.0628   0.0149   1.0000
   9.500   1.3341   0.02127   0.01429  -0.0606   0.0141   1.0000
   9.750   1.3450   0.02227   0.01537  -0.0581   0.0135   1.0000
  10.000   1.3519   0.02336   0.01654  -0.0549   0.0129   1.0000
  10.250   1.3538   0.02480   0.01807  -0.0513   0.0122   1.0000
  10.500   1.3497   0.02686   0.02027  -0.0472   0.0117   1.0000
  10.750   1.3515   0.02872   0.02224  -0.0441   0.0115   1.0000
  11.000   1.3604   0.02990   0.02355  -0.0421   0.0113   1.0000
  11.250   1.3672   0.03138   0.02514  -0.0399   0.0112   1.0000
  11.500   1.3731   0.03299   0.02688  -0.0379   0.0109   1.0000
  11.750   1.3784   0.03475   0.02877  -0.0360   0.0106   1.0000
  12.000   1.3824   0.03679   0.03095  -0.0342   0.0105   1.0000
  12.250   1.3856   0.03896   0.03326  -0.0326   0.0102   1.0000
  12.500   1.3880   0.04126   0.03573  -0.0311   0.0100   1.0000
  12.750   1.3890   0.04385   0.03848  -0.0297   0.0100   1.0000
  13.000   1.3882   0.04665   0.04145  -0.0285   0.0098   1.0000
  13.250   1.3859   0.04973   0.04471  -0.0276   0.0097   1.0000
  13.500   1.3828   0.05284   0.04796  -0.0271   0.0095   1.0000
  13.750   1.3802   0.05587   0.05111  -0.0269   0.0093   1.0000
  14.000   1.3711   0.06013   0.05559  -0.0269   0.0093   1.0000
  14.250   1.3670   0.06358   0.05913  -0.0274   0.0091   1.0000
  14.500   1.3587   0.06786   0.06356  -0.0283   0.0090   1.0000
  14.750   1.3464   0.07306   0.06896  -0.0297   0.0090   1.0000
  15.000   1.3399   0.07739   0.07337  -0.0314   0.0087   1.0000
  15.250   1.3252   0.08360   0.07978  -0.0340   0.0087   1.0000
  15.500   1.3074   0.09079   0.08722  -0.0373   0.0089   1.0000
  15.750   1.2975   0.09650   0.09302  -0.0403   0.0087   1.0000
  16.000   1.2812   0.10397   0.10068  -0.0444   0.0088   1.0000
  16.250   1.2553   0.11409   0.11106  -0.0503   0.0090   1.0000
  16.500   1.2426   0.12141   0.11851  -0.0547   0.0090   1.0000
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