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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 200,000
Max Cl/Cd: 69.55 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe415-il-200000-n5.txt
Download as CSV file: xf-goe415-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2766   0.08471   0.08166  -0.0178   1.0000   0.0202
  -8.000  -0.2757   0.08138   0.07837  -0.0195   1.0000   0.0213
  -7.750  -0.2754   0.07808   0.07511  -0.0215   1.0000   0.0218
  -7.500  -0.2752   0.07475   0.07182  -0.0232   1.0000   0.0220
  -7.250  -0.2757   0.07141   0.06853  -0.0246   1.0000   0.0221
  -7.000  -0.2785   0.06824   0.06543  -0.0255   1.0000   0.0222
  -6.750  -0.2805   0.06496   0.06220  -0.0269   1.0000   0.0223
  -6.500  -0.2821   0.06158   0.05887  -0.0285   1.0000   0.0223
  -6.250  -0.2657   0.05612   0.05338  -0.0350   0.9928   0.0224
  -6.000  -0.2444   0.05024   0.04743  -0.0419   0.9843   0.0224
  -5.750  -0.2219   0.04432   0.04140  -0.0481   0.9751   0.0225
  -5.500  -0.1981   0.03863   0.03555  -0.0533   0.9657   0.0225
  -5.250  -0.1740   0.03326   0.02998  -0.0576   0.9554   0.0226
  -5.000  -0.1494   0.02835   0.02486  -0.0610   0.9442   0.0226
  -4.750  -0.1278   0.02298   0.01935  -0.0636   0.9330   0.0220
  -4.500  -0.1360   0.03563   0.03161  -0.0655   0.9506   0.0159
  -4.250  -0.0942   0.03064   0.02593  -0.0674   0.9402   0.0123
  -3.750  -0.0318   0.02462   0.01905  -0.0697   0.9130   0.0122
  -3.500  -0.0046   0.02131   0.01531  -0.0703   0.8974   0.0137
  -3.250   0.0228   0.01962   0.01328  -0.0700   0.8788   0.0145
  -3.000   0.0505   0.01789   0.01115  -0.0693   0.8583   0.0147
  -2.750   0.0774   0.01649   0.00943  -0.0684   0.8328   0.0151
  -2.500   0.1039   0.01535   0.00797  -0.0674   0.7995   0.0160
  -2.250   0.1298   0.01463   0.00695  -0.0663   0.7598   0.0186
  -2.000   0.1553   0.01390   0.00591  -0.0652   0.7223   0.0205
  -1.750   0.1809   0.01334   0.00508  -0.0643   0.6889   0.0221
  -1.500   0.2062   0.01271   0.00429  -0.0636   0.6582   0.0266
  -1.250   0.2324   0.01238   0.00373  -0.0631   0.6295   0.0309
  -1.000   0.2588   0.01211   0.00324  -0.0627   0.6039   0.0382
  -0.750   0.2856   0.01199   0.00287  -0.0622   0.5820   0.0451
  -0.500   0.3110   0.01118   0.00261  -0.0621   0.5638   0.2387
  -0.250   0.3351   0.01054   0.00260  -0.0616   0.5477   0.4761
   0.000   0.3704   0.00934   0.00252  -0.0626   0.5318   1.0000
   0.250   0.3973   0.00950   0.00245  -0.0623   0.5178   1.0000
   0.500   0.4242   0.00966   0.00242  -0.0621   0.5048   1.0000
   0.750   0.4511   0.00982   0.00241  -0.0618   0.4928   1.0000
   1.000   0.4781   0.00998   0.00242  -0.0616   0.4812   1.0000
   1.250   0.5051   0.01013   0.00245  -0.0614   0.4691   1.0000
   1.500   0.5321   0.01029   0.00249  -0.0612   0.4568   1.0000
   1.750   0.5590   0.01045   0.00255  -0.0610   0.4443   1.0000
   2.000   0.5859   0.01061   0.00262  -0.0608   0.4320   1.0000
   2.250   0.6127   0.01079   0.00272  -0.0606   0.4203   1.0000
   2.500   0.6395   0.01098   0.00282  -0.0604   0.4089   1.0000
   2.750   0.6662   0.01116   0.00294  -0.0602   0.3969   1.0000
   3.000   0.6928   0.01136   0.00309  -0.0600   0.3845   1.0000
   3.250   0.7194   0.01157   0.00324  -0.0598   0.3720   1.0000
   3.500   0.7457   0.01179   0.00341  -0.0595   0.3598   1.0000
   3.750   0.7720   0.01203   0.00359  -0.0593   0.3481   1.0000
   4.000   0.7982   0.01228   0.00382  -0.0591   0.3380   1.0000
   4.250   0.8247   0.01251   0.00406  -0.0589   0.3287   1.0000
   4.500   0.8509   0.01277   0.00431  -0.0586   0.3211   1.0000
   4.750   0.8770   0.01303   0.00460  -0.0584   0.3121   1.0000
   5.000   0.9031   0.01329   0.00489  -0.0582   0.3024   1.0000
   5.250   0.9289   0.01359   0.00519  -0.0579   0.2939   1.0000
   5.500   0.9549   0.01385   0.00554  -0.0577   0.2854   1.0000
   5.750   0.9807   0.01414   0.00589  -0.0574   0.2767   1.0000
   6.000   1.0057   0.01446   0.00619  -0.0571   0.2569   1.0000
   6.250   1.0303   0.01484   0.00653  -0.0567   0.2353   1.0000
   6.500   1.0534   0.01541   0.00692  -0.0563   0.1923   1.0000
   6.750   1.0714   0.01679   0.00779  -0.0555   0.1132   1.0000
   7.000   1.0838   0.01909   0.00949  -0.0539   0.0190   1.0000
   7.250   1.1062   0.01985   0.01042  -0.0531   0.0152   1.0000
   7.500   1.1278   0.02068   0.01146  -0.0523   0.0127   1.0000
   7.750   1.1478   0.02169   0.01270  -0.0512   0.0110   1.0000
   8.000   1.1655   0.02297   0.01424  -0.0500   0.0101   1.0000
   8.250   1.1787   0.02470   0.01627  -0.0483   0.0094   1.0000
   8.500   1.1938   0.02600   0.01779  -0.0469   0.0087   1.0000
   8.750   1.2086   0.02723   0.01916  -0.0455   0.0079   1.0000
   9.000   1.2187   0.02880   0.02087  -0.0437   0.0074   1.0000
   9.250   1.2255   0.03054   0.02273  -0.0416   0.0072   1.0000
   9.500   1.2288   0.03232   0.02461  -0.0391   0.0070   1.0000
   9.750   1.2302   0.03423   0.02662  -0.0367   0.0068   1.0000
  10.000   1.2311   0.03635   0.02884  -0.0347   0.0066   1.0000
  10.250   1.2322   0.03865   0.03122  -0.0330   0.0065   1.0000
  10.500   1.2341   0.04106   0.03371  -0.0317   0.0064   1.0000
  10.750   1.2372   0.04355   0.03628  -0.0304   0.0063   1.0000
  11.000   1.2421   0.04607   0.03885  -0.0290   0.0062   1.0000
  11.250   1.2493   0.04879   0.04161  -0.0275   0.0060   1.0000
  11.500   1.2518   0.05169   0.04468  -0.0266   0.0058   1.0000
  11.750   1.2502   0.05462   0.04787  -0.0267   0.0056   1.0000
  12.000   1.2485   0.05788   0.05137  -0.0271   0.0053   1.0000
  12.250   1.2465   0.06141   0.05511  -0.0275   0.0051   1.0000
  12.500   1.2430   0.06524   0.05915  -0.0282   0.0050   1.0000
  12.750   1.2383   0.06938   0.06349  -0.0291   0.0049   1.0000
  13.000   1.2320   0.07383   0.06814  -0.0303   0.0049   1.0000
  13.250   1.2243   0.07861   0.07311  -0.0319   0.0049   1.0000
  13.500   1.2152   0.08369   0.07839  -0.0338   0.0049   1.0000
  13.750   1.2048   0.08905   0.08394  -0.0361   0.0049   1.0000
  14.000   1.1936   0.09474   0.08980  -0.0387   0.0049   1.0000
  14.250   1.1821   0.10070   0.09594  -0.0416   0.0049   1.0000
  14.500   1.1701   0.10696   0.10237  -0.0449   0.0049   1.0000
  14.750   1.1582   0.11349   0.10907  -0.0485   0.0050   1.0000
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