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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 50,000
Max Cl/Cd: 38.63 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe335-il-50000.txt
Download as CSV file: xf-goe335-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 335 (D.F.W.) AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3300   0.10205   0.09549  -0.0220   1.0000   0.1302
  -7.500  -0.3406   0.10160   0.09520  -0.0226   1.0000   0.1331
  -7.250  -0.3495   0.10184   0.09559  -0.0267   1.0000   0.1342
  -7.000  -0.3298   0.09458   0.08833  -0.0211   1.0000   0.1411
  -6.750  -0.3325   0.09314   0.08700  -0.0229   1.0000   0.1466
  -6.500  -0.3324   0.09068   0.08466  -0.0243   1.0000   0.1499
  -6.250  -0.3256   0.08728   0.08129  -0.0222   1.0000   0.1588
  -6.000  -0.3268   0.08574   0.07986  -0.0254   1.0000   0.1637
  -5.750  -0.3213   0.08231   0.07649  -0.0225   1.0000   0.1736
  -5.000  -0.3143   0.07462   0.06903  -0.0210   1.0000   0.1984
  -4.750  -0.3114   0.07239   0.06684  -0.0219   1.0000   0.2086
  -4.500  -0.3066   0.07027   0.06473  -0.0226   1.0000   0.2216
  -4.250  -0.3014   0.06780   0.06229  -0.0222   1.0000   0.2358
  -4.000  -0.2963   0.06510   0.05962  -0.0209   1.0000   0.2509
  -3.750  -0.2911   0.06239   0.05695  -0.0190   1.0000   0.2680
  -3.500  -0.2840   0.05993   0.05448  -0.0184   1.0000   0.2948
  -3.250  -0.2800   0.05735   0.05196  -0.0156   1.0000   0.3260
  -3.000  -0.2770   0.05486   0.04955  -0.0126   1.0000   0.3674
  -2.750  -0.2779   0.05248   0.04726  -0.0082   1.0000   0.4218
  -2.500  -0.2816   0.04985   0.04477  -0.0016   1.0000   0.4700
  -2.250  -0.2835   0.04741   0.04243   0.0041   1.0000   0.5236
  -2.000  -0.2841   0.04490   0.04003   0.0099   1.0000   0.5691
  -1.750  -0.2799   0.04244   0.03764   0.0140   1.0000   0.6110
  -1.500  -0.2716   0.04002   0.03526   0.0170   1.0000   0.6457
  -1.250  -0.2565   0.03762   0.03288   0.0177   1.0000   0.6780
  -1.000   0.0083   0.03514   0.02691  -0.0483   1.0000   0.2013
  -0.750   0.0370   0.03385   0.02512  -0.0493   1.0000   0.1891
  -0.500   0.0756   0.03266   0.02332  -0.0516   0.9958   0.1765
  -0.250   0.1369   0.03117   0.02136  -0.0580   0.9806   0.1698
   0.000   0.1946   0.03022   0.01995  -0.0635   0.9629   0.1699
   0.250   0.2552   0.02952   0.01891  -0.0693   0.9447   0.1854
   0.500   0.3157   0.02868   0.01783  -0.0746   0.9261   0.2011
   0.750   0.3683   0.02775   0.01703  -0.0786   0.9053   0.2411
   1.000   0.4332   0.02502   0.01560  -0.0837   0.8878   1.0000
   1.250   0.4850   0.02506   0.01527  -0.0875   0.8636   1.0000
   1.500   0.5483   0.02472   0.01467  -0.0926   0.8441   1.0000
   1.750   0.5902   0.02470   0.01452  -0.0941   0.8192   1.0000
   2.000   0.6313   0.02469   0.01439  -0.0953   0.7964   1.0000
   2.250   0.6697   0.02471   0.01430  -0.0959   0.7748   1.0000
   2.500   0.6982   0.02509   0.01461  -0.0953   0.7524   1.0000
   2.750   0.7283   0.02540   0.01487  -0.0949   0.7330   1.0000
   3.000   0.7584   0.02568   0.01509  -0.0944   0.7159   1.0000
   3.250   0.7810   0.02638   0.01578  -0.0934   0.6979   1.0000
   3.500   0.8049   0.02705   0.01644  -0.0925   0.6823   1.0000
   3.750   0.8292   0.02773   0.01717  -0.0917   0.6679   1.0000
   4.000   0.8537   0.02842   0.01789  -0.0910   0.6549   1.0000
   4.250   0.8801   0.02901   0.01850  -0.0904   0.6432   1.0000
   4.500   0.9031   0.02986   0.01941  -0.0897   0.6312   1.0000
   4.750   0.9229   0.03097   0.02062  -0.0888   0.6189   1.0000
   5.000   0.9426   0.03210   0.02192  -0.0879   0.6069   1.0000
   5.250   0.9638   0.03309   0.02302  -0.0869   0.5952   1.0000
   5.500   0.9876   0.03386   0.02390  -0.0860   0.5840   1.0000
   5.750   1.0155   0.03432   0.02446  -0.0853   0.5736   1.0000
   6.000   1.0294   0.03603   0.02642  -0.0841   0.5618   1.0000
   6.250   1.0440   0.03777   0.02836  -0.0830   0.5508   1.0000
   6.500   1.0638   0.03910   0.02988  -0.0821   0.5408   1.0000
   6.750   1.0926   0.03964   0.03060  -0.0814   0.5310   1.0000
   7.000   1.0970   0.04243   0.03364  -0.0800   0.5198   1.0000
   7.250   1.1031   0.04516   0.03659  -0.0788   0.5091   1.0000
   7.500   1.1193   0.04677   0.03849  -0.0774   0.4972   1.0000
   7.750   1.1391   0.04780   0.03977  -0.0758   0.4834   1.0000
   8.000   1.2138   0.03957   0.03157  -0.0714   0.4384   1.0000
   8.250   1.2488   0.03480   0.02655  -0.0668   0.3851   1.0000
   8.500   1.2554   0.03284   0.02464  -0.0613   0.3352   1.0000
   8.750   1.2435   0.03219   0.02412  -0.0544   0.2637   1.0000
   9.000   1.2236   0.03430   0.02526  -0.0483   0.1686   1.0000
   9.250   1.2119   0.03761   0.02801  -0.0441   0.1336   1.0000
   9.500   1.2064   0.04043   0.03064  -0.0407   0.1167   1.0000
   9.750   1.2049   0.04313   0.03325  -0.0380   0.1052   1.0000
  10.000   1.2079   0.04580   0.03589  -0.0357   0.0959   1.0000
  10.250   1.2277   0.04842   0.03836  -0.0340   0.0877   1.0000
  10.500   1.2676   0.05150   0.04172  -0.0337   0.0814   1.0000
  10.750   1.3189   0.05687   0.04716  -0.0358   0.0760   1.0000
  11.000   1.3204   0.06003   0.05083  -0.0334   0.0747   1.0000
  11.250   1.3173   0.06342   0.05466  -0.0310   0.0736   1.0000
  11.500   1.3099   0.06699   0.05859  -0.0286   0.0730   1.0000
  11.750   1.2993   0.07082   0.06276  -0.0266   0.0728   1.0000
  12.000   1.2849   0.07500   0.06725  -0.0253   0.0729   1.0000
  12.250   1.2683   0.07956   0.07208  -0.0248   0.0734   1.0000
  12.500   1.2486   0.08465   0.07742  -0.0253   0.0738   1.0000
  12.750   1.2280   0.09028   0.08326  -0.0267   0.0743   1.0000
  13.000   1.2073   0.09648   0.08965  -0.0290   0.0750   1.0000
  13.250   1.1872   0.10327   0.09657  -0.0320   0.0756   1.0000
  13.500   1.1706   0.11040   0.10381  -0.0352   0.0763   1.0000
  13.750   1.0807   0.13240   0.12597  -0.0541   0.0876   1.0000
  14.000   1.0736   0.14012   0.13367  -0.0574   0.0888   1.0000
  14.250   1.0256   0.16062   0.15396  -0.0720   0.0991   1.0000
  14.500   1.0325   0.16587   0.15923  -0.0730   0.1010   1.0000
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