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GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 373 AIRFOIL (goe373-il)
Reynolds number: 500,000
Max Cl/Cd: 105.95 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe373-il-500000.txt
Download as CSV file: xf-goe373-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 373 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3042   0.09778   0.09558  -0.0237   1.0000   0.0159
  -8.000  -0.3083   0.09597   0.09382  -0.0238   1.0000   0.0159
  -7.750  -0.3137   0.09418   0.09208  -0.0231   1.0000   0.0159
  -7.500  -0.3109   0.09066   0.08860  -0.0221   1.0000   0.0160
  -7.250  -0.3063   0.08752   0.08548  -0.0198   1.0000   0.0162
  -7.000  -0.3058   0.08522   0.08322  -0.0185   1.0000   0.0164
  -6.750  -0.3053   0.08310   0.08114  -0.0182   0.9998   0.0165
  -6.500  -0.2768   0.07888   0.07689  -0.0252   0.9962   0.0170
  -6.250  -0.2468   0.07459   0.07259  -0.0326   0.9914   0.0177
  -6.000  -0.2126   0.07014   0.06810  -0.0411   0.9859   0.0188
  -5.750  -0.1605   0.06508   0.06294  -0.0561   0.9785   0.0194
  -5.500  -0.1115   0.05977   0.05750  -0.0681   0.9720   0.0195
  -5.250  -0.0868   0.05483   0.05254  -0.0718   0.9646   0.0197
  -5.000  -0.0595   0.05132   0.04901  -0.0751   0.9568   0.0199
  -4.750  -0.0276   0.04803   0.04565  -0.0795   0.9446   0.0203
  -4.500   0.0084   0.04469   0.04222  -0.0847   0.9298   0.0209
  -4.250   0.0440   0.04155   0.03893  -0.0893   0.9098   0.0219
  -4.000   0.0823   0.03856   0.03568  -0.0932   0.8860   0.0233
  -3.750   0.1200   0.03584   0.03258  -0.0957   0.8648   0.0237
  -3.500   0.1480   0.03342   0.02986  -0.0966   0.8464   0.0237
  -3.250   0.1680   0.03005   0.02639  -0.0973   0.8299   0.0240
  -3.000   0.1895   0.02820   0.02445  -0.0975   0.8141   0.0244
  -2.750   0.2132   0.02659   0.02269  -0.0978   0.7991   0.0248
  -2.500   0.2387   0.02497   0.02089  -0.0979   0.7849   0.0254
  -2.250   0.2651   0.02338   0.01910  -0.0980   0.7712   0.0262
  -2.000   0.2927   0.02184   0.01734  -0.0978   0.7581   0.0275
  -1.750   0.3249   0.02139   0.01636  -0.0968   0.7451   0.0289
  -1.500   0.3493   0.01873   0.01354  -0.0969   0.7318   0.0295
  -1.250   0.3741   0.01749   0.01220  -0.0969   0.7173   0.0301
  -1.000   0.3996   0.01658   0.01116  -0.0966   0.7017   0.0310
  -0.750  -0.4998   0.04168   0.03862   0.0631   0.7888   0.0237
  -0.500   0.4534   0.01549   0.00962  -0.0955   0.6679   0.0348
   1.500  -0.1826   0.01408   0.01011  -0.0189   0.7019   0.0246
   2.000   0.7130   0.01074   0.00364  -0.0914   0.5055   0.0969
   2.250   0.7408   0.01068   0.00345  -0.0905   0.4937   0.0655
   2.500   0.7671   0.01045   0.00316  -0.0899   0.4812   0.0545
   2.750   0.7929   0.01015   0.00284  -0.0893   0.4679   0.0488
   3.000   0.8192   0.01017   0.00280  -0.0888   0.4548   0.0448
   3.250   0.8453   0.01016   0.00277  -0.0884   0.4412   0.0432
   3.500   0.8713   0.01016   0.00273  -0.0880   0.4276   0.0424
   3.750   0.8973   0.01023   0.00274  -0.0875   0.4136   0.0424
   4.000   0.9231   0.01034   0.00278  -0.0871   0.3997   0.0431
   4.250   0.9486   0.01048   0.00285  -0.0866   0.3826   0.0461
   4.500   0.9736   0.01070   0.00297  -0.0861   0.3608   0.0473
   4.750   0.9985   0.01093   0.00312  -0.0856   0.3437   0.0494
   5.000   1.0277   0.00970   0.00352  -0.0865   0.3292   1.0000
   5.250   1.0526   0.00996   0.00372  -0.0859   0.3141   1.0000
   5.500   1.0774   0.01023   0.00392  -0.0854   0.2978   1.0000
   5.750   1.1021   0.01052   0.00412  -0.0849   0.2755   1.0000
   6.000   1.1254   0.01094   0.00436  -0.0842   0.2406   1.0000
   6.250   1.1438   0.01192   0.00488  -0.0830   0.1698   1.0000
   6.500   1.1644   0.01265   0.00540  -0.0820   0.1359   1.0000
   6.750   1.1848   0.01341   0.00590  -0.0809   0.0967   1.0000
   7.000   1.2015   0.01457   0.00672  -0.0794   0.0463   1.0000
   7.250   1.2205   0.01545   0.00746  -0.0780   0.0201   1.0000
   7.500   1.2422   0.01600   0.00809  -0.0770   0.0182   1.0000
   7.750   1.2634   0.01660   0.00876  -0.0760   0.0165   1.0000
   8.000   1.2841   0.01723   0.00950  -0.0748   0.0155   1.0000
   8.250   1.3042   0.01787   0.01024  -0.0736   0.0151   1.0000
   8.500   1.3232   0.01860   0.01107  -0.0723   0.0147   1.0000
   8.750   1.3407   0.01943   0.01200  -0.0707   0.0143   1.0000
   9.000   1.3564   0.02035   0.01301  -0.0690   0.0139   1.0000
   9.250   1.3701   0.02137   0.01412  -0.0669   0.0136   1.0000
   9.500   1.3811   0.02251   0.01535  -0.0646   0.0131   1.0000
   9.750   1.3884   0.02374   0.01666  -0.0617   0.0127   1.0000
  10.000   1.3909   0.02501   0.01800  -0.0581   0.0124   1.0000
  10.250   1.3888   0.02663   0.01970  -0.0542   0.0121   1.0000
  10.500   1.3876   0.02836   0.02150  -0.0509   0.0119   1.0000
  10.750   1.3866   0.03029   0.02351  -0.0480   0.0118   1.0000
  11.000   1.3871   0.03241   0.02568  -0.0456   0.0117   1.0000
  11.250   1.3916   0.03452   0.02784  -0.0437   0.0116   1.0000
  11.500   1.4003   0.03646   0.02984  -0.0421   0.0116   1.0000
  11.750   1.4138   0.03849   0.03191  -0.0409   0.0115   1.0000
  12.000   1.4274   0.04032   0.03381  -0.0398   0.0116   1.0000
  12.250   1.4395   0.04215   0.03573  -0.0386   0.0116   1.0000
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