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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 500,000
Max Cl/Cd: 105.99 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe379-il-500000.txt
Download as CSV file: xf-goe379-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3068   0.09121   0.08917  -0.0251   1.0000   0.0113
  -7.250  -0.3126   0.08938   0.08740  -0.0239   1.0000   0.0113
  -7.000  -0.3132   0.08718   0.08525  -0.0239   0.9994   0.0113
  -6.750  -0.2835   0.08214   0.08019  -0.0325   0.9948   0.0114
  -6.500  -0.2709   0.07604   0.07410  -0.0349   0.9903   0.0121
  -6.250  -0.2459   0.07255   0.07059  -0.0395   0.9855   0.0130
  -6.000  -0.2168   0.06842   0.06644  -0.0462   0.9797   0.0138
  -5.750  -0.1859   0.06418   0.06215  -0.0530   0.9729   0.0148
  -5.500  -0.1493   0.05965   0.05756  -0.0609   0.9676   0.0158
  -5.250  -0.1056   0.05553   0.05333  -0.0697   0.9583   0.0170
  -5.000  -0.0675   0.05182   0.04949  -0.0756   0.9482   0.0174
  -4.750  -0.0340   0.04794   0.04549  -0.0800   0.9357   0.0175
  -4.500  -0.0054   0.04434   0.04174  -0.0828   0.9195   0.0175
  -4.250   0.0099   0.03891   0.03616  -0.0845   0.9019   0.0187
  -4.000   0.0306   0.03674   0.03386  -0.0847   0.8853   0.0194
  -3.750   0.0530   0.03446   0.03142  -0.0849   0.8701   0.0205
  -3.500   0.0771   0.03201   0.02879  -0.0850   0.8568   0.0224
  -2.250   0.1942   0.01254   0.00697  -0.0786   0.7988   0.0186
  -2.000   0.2190   0.01109   0.00516  -0.0776   0.7870   0.0197
  -1.750   0.2448   0.01047   0.00437  -0.0769   0.7751   0.0217
  -1.500   0.2705   0.00994   0.00368  -0.0761   0.7625   0.0243
  -1.250   0.2956   0.00942   0.00303  -0.0753   0.7494   0.0290
  -1.000   0.3216   0.00927   0.00281  -0.0747   0.7358   0.0357
  -0.750   0.3474   0.00913   0.00259  -0.0741   0.7218   0.0468
  -0.500   0.3730   0.00902   0.00242  -0.0735   0.7077   0.0562
  -0.250   0.3991   0.00904   0.00235  -0.0730   0.6931   0.0625
   0.000   0.4242   0.00890   0.00216  -0.0724   0.6779   0.0706
   0.250   0.4497   0.00884   0.00200  -0.0718   0.6618   0.0755
   0.500   0.4746   0.00868   0.00179  -0.0711   0.6452   0.0814
   0.750   0.5000   0.00868   0.00172  -0.0705   0.6287   0.0895
   1.000   0.5250   0.00861   0.00162  -0.0699   0.6125   0.1002
   1.250   0.5498   0.00857   0.00155  -0.0692   0.5957   0.1208
   1.500   0.5705   0.00801   0.00164  -0.0681   0.5791   0.4124
   1.750   0.6700   0.00699   0.00171  -0.0847   0.5531   1.0000
   2.000   0.6947   0.00713   0.00176  -0.0840   0.5386   1.0000
   2.250   0.7193   0.00728   0.00181  -0.0833   0.5243   1.0000
   2.500   0.7439   0.00744   0.00188  -0.0826   0.5100   1.0000
   2.750   0.7684   0.00759   0.00197  -0.0820   0.4957   1.0000
   3.000   0.7928   0.00775   0.00206  -0.0813   0.4805   1.0000
   3.250   0.8172   0.00791   0.00218  -0.0806   0.4651   1.0000
   3.500   0.8416   0.00808   0.00229  -0.0799   0.4506   1.0000
   3.750   0.8658   0.00826   0.00242  -0.0792   0.4368   1.0000
   4.000   0.8900   0.00844   0.00256  -0.0786   0.4237   1.0000
   4.250   0.9141   0.00864   0.00272  -0.0779   0.4113   1.0000
   4.500   0.9380   0.00885   0.00292  -0.0771   0.3972   1.0000
   4.750   0.9614   0.00908   0.00309  -0.0763   0.3792   1.0000
   5.000   0.9848   0.00931   0.00329  -0.0756   0.3640   1.0000
   5.250   1.0073   0.00961   0.00350  -0.0746   0.3426   1.0000
   5.500   1.0302   0.00989   0.00372  -0.0738   0.3227   1.0000
   5.750   1.0526   0.01021   0.00400  -0.0729   0.3016   1.0000
   6.000   1.0728   0.01071   0.00430  -0.0716   0.2535   1.0000
   6.250   1.0774   0.01272   0.00533  -0.0682   0.0967   1.0000
   6.500   1.0877   0.01424   0.00647  -0.0653   0.0213   1.0000
   6.750   1.1070   0.01488   0.00722  -0.0637   0.0173   1.0000
   7.000   1.1238   0.01576   0.00828  -0.0617   0.0151   1.0000
   7.250   1.1428   0.01635   0.00897  -0.0602   0.0141   1.0000
   7.500   1.1593   0.01715   0.00988  -0.0583   0.0131   1.0000
   7.750   1.1739   0.01805   0.01089  -0.0560   0.0124   1.0000
   8.000   1.1860   0.01910   0.01204  -0.0534   0.0117   1.0000
   8.250   1.1964   0.02020   0.01325  -0.0506   0.0112   1.0000
   8.500   1.2041   0.02146   0.01460  -0.0474   0.0109   1.0000
   8.750   1.2097   0.02283   0.01607  -0.0439   0.0107   1.0000
   9.000   1.2138   0.02414   0.01747  -0.0402   0.0107   1.0000
   9.250   1.2190   0.02557   0.01900  -0.0368   0.0105   1.0000
   9.500   1.2259   0.02711   0.02059  -0.0341   0.0101   1.0000
   9.750   1.2402   0.03025   0.02376  -0.0327   0.0093   1.0000
  10.000   1.2559   0.03173   0.02535  -0.0310   0.0095   1.0000
  10.250   1.2810   0.03483   0.02861  -0.0311   0.0095   1.0000
  10.500   1.2516   0.03878   0.03361  -0.0262   0.0151   1.0000
  10.750   1.2478   0.04164   0.03669  -0.0229   0.0151   1.0000
  11.000   1.2369   0.04390   0.03915  -0.0185   0.0151   1.0000
  11.250   1.2217   0.04572   0.04114  -0.0141   0.0150   1.0000
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