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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 200,000
Max Cl/Cd: 77.67 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe379-il-200000.txt
Download as CSV file: xf-goe379-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.3109   0.09130   0.08828  -0.0291   1.0000   0.0261
  -6.500  -0.3148   0.08960   0.08663  -0.0279   1.0000   0.0261
  -6.250  -0.3255   0.08568   0.08280  -0.0252   1.0000   0.0264
  -6.000  -0.3244   0.08119   0.07835  -0.0224   0.9988   0.0271
  -5.750  -0.2993   0.07650   0.07364  -0.0260   0.9945   0.0281
  -5.500  -0.2691   0.07218   0.06929  -0.0320   0.9883   0.0294
  -5.250  -0.2326   0.06770   0.06474  -0.0397   0.9832   0.0311
  -5.000  -0.1976   0.06352   0.06048  -0.0467   0.9755   0.0332
  -4.750  -0.1331   0.06014   0.05684  -0.0602   0.9699   0.0365
  -4.500  -0.0495   0.03427   0.03110  -0.0712   0.9483   0.0383
  -4.250  -0.0228   0.03011   0.02690  -0.0737   0.9432   0.0403
  -4.000   0.0049   0.02672   0.02341  -0.0765   0.9344   0.0432
  -3.750   0.0577   0.02486   0.02104  -0.0823   0.9277   0.0494
  -3.500   0.0689   0.01969   0.01594  -0.0826   0.9167   0.0516
  -3.250   0.0907   0.01719   0.01334  -0.0827   0.9049   0.0543
  -3.000   0.1158   0.01503   0.01096  -0.0829   0.8929   0.0585
  -2.750   0.1465   0.01302   0.00841  -0.0830   0.8818   0.0638
  -2.500   0.1664   0.01076   0.00611  -0.0826   0.8718   0.0659
  -2.250   0.1885   0.00935   0.00453  -0.0818   0.8597   0.0698
  -2.000   0.2247   0.02411   0.01846  -0.0856   0.8757   0.0778
  -1.750   0.2523   0.01948   0.01321  -0.0835   0.8648   0.0484
  -1.500   0.2784   0.01714   0.01042  -0.0823   0.8533   0.0478
  -1.250   0.3053   0.01529   0.00810  -0.0812   0.8416   0.0508
  -1.000   0.3314   0.01485   0.00750  -0.0805   0.8286   0.0616
  -0.750   0.3577   0.01382   0.00630  -0.0796   0.8157   0.0715
  -0.500   0.3834   0.01338   0.00572  -0.0788   0.8017   0.0857
  -0.250   0.4089   0.01291   0.00516  -0.0781   0.7875   0.0975
   0.000   0.4346   0.01255   0.00465  -0.0772   0.7731   0.1046
   0.250   0.4593   0.01214   0.00424  -0.0763   0.7581   0.1151
   0.500   0.4837   0.01180   0.00389  -0.0754   0.7427   0.1254
   0.750   0.5080   0.01153   0.00361  -0.0744   0.7271   0.1395
   1.000   0.5322   0.01130   0.00342  -0.0735   0.7118   0.1680
   1.250   0.6199   0.00942   0.00311  -0.0868   0.6933   1.0000
   1.500   0.6443   0.00955   0.00307  -0.0859   0.6769   1.0000
   1.750   0.6685   0.00969   0.00308  -0.0850   0.6595   1.0000
   2.000   0.6927   0.00984   0.00312  -0.0841   0.6428   1.0000
   2.250   0.7169   0.01001   0.00316  -0.0832   0.6265   1.0000
   2.500   0.7409   0.01020   0.00322  -0.0823   0.6097   1.0000
   2.750   0.7647   0.01040   0.00330  -0.0814   0.5919   1.0000
   3.000   0.7883   0.01060   0.00342  -0.0805   0.5740   1.0000
   3.250   0.8119   0.01083   0.00358  -0.0796   0.5570   1.0000
   3.500   0.8355   0.01109   0.00373  -0.0787   0.5406   1.0000
   3.750   0.8590   0.01136   0.00391  -0.0778   0.5249   1.0000
   4.000   0.8826   0.01161   0.00412  -0.0770   0.5095   1.0000
   4.250   0.9062   0.01189   0.00436  -0.0761   0.4956   1.0000
   4.500   0.9299   0.01218   0.00466  -0.0753   0.4826   1.0000
   4.750   0.9536   0.01246   0.00494  -0.0746   0.4699   1.0000
   5.000   0.9771   0.01273   0.00523  -0.0737   0.4573   1.0000
   5.250   1.0006   0.01301   0.00556  -0.0729   0.4453   1.0000
   5.500   1.0226   0.01326   0.00577  -0.0718   0.4287   1.0000
   5.750   1.0440   0.01345   0.00604  -0.0706   0.4082   1.0000
   6.000   1.0648   0.01371   0.00627  -0.0693   0.3877   1.0000
   6.250   1.0851   0.01398   0.00655  -0.0679   0.3625   1.0000
   6.500   1.1042   0.01434   0.00686  -0.0664   0.3327   1.0000
   6.750   1.1208   0.01488   0.00725  -0.0644   0.2784   1.0000
   7.000   1.1234   0.01686   0.00825  -0.0608   0.1315   1.0000
   7.250   1.1240   0.01927   0.01001  -0.0568   0.0343   1.0000
   7.500   1.1401   0.02020   0.01111  -0.0547   0.0299   1.0000
   7.750   1.1543   0.02123   0.01234  -0.0524   0.0276   1.0000
   8.000   1.1639   0.02253   0.01382  -0.0495   0.0259   1.0000
   8.250   1.1662   0.02422   0.01566  -0.0458   0.0242   1.0000
   8.500   1.1714   0.02560   0.01715  -0.0425   0.0230   1.0000
   8.750   1.1749   0.02698   0.01863  -0.0388   0.0224   1.0000
   9.000   1.1789   0.02850   0.02024  -0.0354   0.0221   1.0000
   9.250   1.1855   0.03024   0.02205  -0.0325   0.0218   1.0000
   9.500   1.1975   0.03211   0.02404  -0.0304   0.0218   1.0000
   9.750   1.2189   0.03447   0.02649  -0.0293   0.0221   1.0000
  10.000   1.2768   0.04059   0.03274  -0.0337   0.0239   1.0000
  10.250   1.2959   0.04352   0.03591  -0.0326   0.0240   1.0000
  10.500   1.3101   0.04610   0.03873  -0.0308   0.0242   1.0000
  16.250   0.8145   0.17673   0.17369  -0.0559   0.0671   1.0000
  16.500   0.7915   0.18237   0.17929  -0.0629   0.0656   1.0000
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