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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 500,000
Max Cl/Cd: 101.47 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe377-il-500000.txt
Download as CSV file: xf-goe377-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3764   0.08542   0.08330  -0.0226   1.0000   0.0156
  -7.250  -0.3873   0.08362   0.08156  -0.0206   1.0000   0.0160
  -7.000  -0.3944   0.08155   0.07953  -0.0195   1.0000   0.0162
  -6.750  -0.4025   0.07949   0.07752  -0.0186   1.0000   0.0168
  -6.500  -0.3777   0.07486   0.07285  -0.0280   0.9974   0.0175
  -6.250  -0.3411   0.06935   0.06726  -0.0376   0.9939   0.0177
  -6.000  -0.3102   0.06413   0.06195  -0.0444   0.9896   0.0178
  -4.000  -0.0398   0.01006   0.00660  -0.0765   0.9561   0.0240
  -3.750  -0.0378   0.02179   0.01774  -0.0754   0.9579   0.0224
  -3.500  -0.0094   0.01819   0.01364  -0.0752   0.9535   0.0235
  -3.000   0.0484   0.01348   0.00812  -0.0752   0.9442   0.0276
  -2.750   0.0774   0.01295   0.00751  -0.0753   0.9388   0.0301
  -2.500   0.1069   0.01253   0.00697  -0.0754   0.9325   0.0339
  -2.250   0.1369   0.01209   0.00637  -0.0754   0.9255   0.0358
  -2.000   0.1636   0.01059   0.00474  -0.0751   0.9157   0.0397
  -1.750   0.1897   0.01018   0.00426  -0.0744   0.9036   0.0424
  -1.500   0.2158   0.00970   0.00371  -0.0737   0.8920   0.0443
  -1.250   0.2422   0.00942   0.00335  -0.0731   0.8811   0.0469
  -1.000   0.2686   0.00919   0.00306  -0.0725   0.8703   0.0482
  -0.750   0.2928   0.00859   0.00240  -0.0716   0.8587   0.0505
  -0.500   0.3177   0.00830   0.00209  -0.0707   0.8461   0.0532
  -0.250   0.3432   0.00812   0.00187  -0.0700   0.8330   0.0565
   0.000   0.3688   0.00800   0.00170  -0.0694   0.8186   0.0615
   0.250   0.3939   0.00781   0.00148  -0.0686   0.8028   0.0747
   0.750   0.5124   0.00557   0.00149  -0.0832   0.7679   1.0000
   1.000   0.5359   0.00567   0.00145  -0.0821   0.7458   1.0000
   1.250   0.5593   0.00578   0.00144  -0.0810   0.7219   1.0000
   1.500   0.5825   0.00592   0.00144  -0.0799   0.6972   1.0000
   1.750   0.6054   0.00608   0.00147  -0.0788   0.6709   1.0000
   2.000   0.6281   0.00625   0.00151  -0.0776   0.6430   1.0000
   2.250   0.6509   0.00644   0.00157  -0.0764   0.6162   1.0000
   2.500   0.6736   0.00664   0.00166  -0.0753   0.5891   1.0000
   2.750   0.6961   0.00686   0.00175  -0.0742   0.5614   1.0000
   3.000   0.7185   0.00710   0.00186  -0.0730   0.5316   1.0000
   3.250   0.7408   0.00735   0.00198  -0.0719   0.5007   1.0000
   3.500   0.7628   0.00763   0.00213  -0.0707   0.4666   1.0000
   3.750   0.7854   0.00789   0.00228  -0.0696   0.4371   1.0000
   4.000   0.8078   0.00817   0.00245  -0.0686   0.4067   1.0000
   4.250   0.8299   0.00848   0.00264  -0.0675   0.3759   1.0000
   4.500   0.8513   0.00886   0.00286  -0.0663   0.3420   1.0000
   4.750   0.8729   0.00924   0.00312  -0.0651   0.3123   1.0000
   5.000   0.8954   0.00954   0.00335  -0.0642   0.2903   1.0000
   5.250   0.9180   0.00985   0.00359  -0.0632   0.2706   1.0000
   5.500   0.9404   0.01017   0.00384  -0.0623   0.2474   1.0000
   5.750   0.9620   0.01056   0.00413  -0.0612   0.2177   1.0000
   6.000   0.9828   0.01104   0.00445  -0.0600   0.1799   1.0000
   6.250   0.9966   0.01219   0.00510  -0.0578   0.0939   1.0000
   6.500   1.0089   0.01359   0.00607  -0.0552   0.0239   1.0000
   6.750   1.0289   0.01421   0.00671  -0.0537   0.0191   1.0000
   7.000   1.0474   0.01500   0.00763  -0.0519   0.0167   1.0000
   7.250   1.0669   0.01564   0.00841  -0.0504   0.0160   1.0000
   7.500   1.0848   0.01642   0.00929  -0.0486   0.0150   1.0000
   7.750   1.1017   0.01725   0.01022  -0.0467   0.0142   1.0000
   8.000   1.1178   0.01812   0.01116  -0.0448   0.0129   1.0000
   8.250   1.1312   0.01924   0.01236  -0.0424   0.0122   1.0000
   8.500   1.1412   0.02071   0.01394  -0.0395   0.0117   1.0000
   8.750   1.1493   0.02269   0.01604  -0.0365   0.0113   1.0000
   9.000   1.1606   0.02524   0.01876  -0.0340   0.0111   1.0000
   9.250   1.1773   0.02596   0.01961  -0.0322   0.0106   1.0000
   9.500   1.1922   0.02813   0.02194  -0.0305   0.0107   1.0000
   9.750   1.2064   0.03029   0.02430  -0.0286   0.0106   1.0000
  10.000   1.2180   0.03390   0.02818  -0.0266   0.0108   1.0000
  10.250   1.2315   0.03755   0.03201  -0.0252   0.0112   1.0000
  10.500   1.2363   0.04046   0.03519  -0.0225   0.0112   1.0000
  10.750   1.2435   0.04184   0.03672  -0.0200   0.0113   1.0000
  11.000   1.2455   0.04336   0.03842  -0.0167   0.0114   1.0000
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