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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 50,000
Max Cl/Cd: 26.12 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe285-il-50000.txt
Download as CSV file: xf-goe285-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3668   0.10963   0.10250  -0.0236   1.0000   0.2343
  -8.250  -0.3309   0.10321   0.09604  -0.0215   1.0000   0.2418
  -8.000  -0.3480   0.10246   0.09543  -0.0219   1.0000   0.2510
  -7.750  -0.3323   0.09813   0.09114  -0.0208   1.0000   0.2575
  -7.500  -0.3433   0.09681   0.08995  -0.0199   1.0000   0.2678
  -7.250  -0.3337   0.09326   0.08646  -0.0185   1.0000   0.2762
  -7.000  -0.3579   0.09277   0.08617  -0.0162   1.0000   0.2860
  -6.750  -0.3413   0.08908   0.08251  -0.0143   1.0000   0.2985
  -6.500  -0.3914   0.08994   0.08365  -0.0129   1.0000   0.3053
  -6.250  -0.3741   0.08639   0.08013  -0.0091   1.0000   0.3213
  -6.000  -0.3671   0.08359   0.07741  -0.0059   1.0000   0.3354
  -5.750  -0.3735   0.08158   0.07552  -0.0027   1.0000   0.3491
  -5.250  -0.3945   0.07822   0.07239   0.0041   1.0000   0.3813
  -5.000  -0.3982   0.07636   0.07063   0.0080   1.0000   0.4007
  -4.750  -0.4035   0.07471   0.06907   0.0121   1.0000   0.4236
  -4.500  -0.4119   0.07305   0.06751   0.0166   1.0000   0.4514
  -4.250  -0.4185   0.07160   0.06617   0.0219   1.0000   0.4852
  -3.750  -0.1957   0.06032   0.05455   0.0227   1.0000   0.7794
  -3.500  -0.1558   0.05688   0.05109   0.0200   1.0000   0.8341
  -3.250  -0.3140   0.04724   0.03948  -0.0291   1.0000   0.1966
  -3.000  -0.2850   0.04394   0.03545  -0.0314   1.0000   0.1810
  -2.750  -0.2631   0.04165   0.03298  -0.0319   1.0000   0.1774
  -2.500  -0.2391   0.03964   0.03061  -0.0325   1.0000   0.1743
  -2.250  -0.2156   0.03814   0.02874  -0.0330   1.0000   0.1755
  -2.000  -0.1921   0.03699   0.02718  -0.0334   1.0000   0.1793
  -1.750  -0.1484   0.03553   0.02538  -0.0372   0.9939   0.1854
  -1.500  -0.0921   0.03440   0.02391  -0.0430   0.9817   0.2014
  -1.250  -0.0399   0.03338   0.02284  -0.0480   0.9687   0.2268
  -1.000   0.0104   0.03266   0.02211  -0.0524   0.9553   0.2663
  -0.750   0.0633   0.03201   0.02157  -0.0571   0.9414   0.3129
  -0.500   0.1141   0.03126   0.02112  -0.0613   0.9273   0.3733
  -0.250   0.1633   0.02869   0.02062  -0.0633   0.9132   1.0000
   0.000   0.2129   0.02920   0.02048  -0.0671   0.8960   1.0000
   0.250   0.2623   0.02957   0.02049  -0.0709   0.8785   1.0000
   0.500   0.3032   0.02985   0.02053  -0.0731   0.8582   1.0000
   0.750   0.3471   0.02993   0.02041  -0.0753   0.8373   1.0000
   1.000   0.3959   0.02975   0.02006  -0.0779   0.8179   1.0000
   1.250   0.4389   0.02955   0.01972  -0.0793   0.7992   1.0000
   1.500   0.4780   0.02940   0.01945  -0.0801   0.7813   1.0000
   1.750   0.5139   0.02929   0.01924  -0.0803   0.7636   1.0000
   2.000   0.5475   0.02921   0.01908  -0.0801   0.7461   1.0000
   2.250   0.5793   0.02917   0.01895  -0.0796   0.7289   1.0000
   2.500   0.6098   0.02915   0.01887  -0.0789   0.7117   1.0000
   2.750   0.6393   0.02918   0.01882  -0.0780   0.6946   1.0000
   3.000   0.6676   0.02928   0.01886  -0.0771   0.6776   1.0000
   3.250   0.6949   0.02948   0.01900  -0.0760   0.6608   1.0000
   3.500   0.7213   0.02976   0.01922  -0.0750   0.6440   1.0000
   3.750   0.7467   0.03015   0.01955  -0.0738   0.6274   1.0000
   4.000   0.7708   0.03069   0.02005  -0.0727   0.6112   1.0000
   4.250   0.7937   0.03139   0.02073  -0.0716   0.5959   1.0000
   4.500   0.8164   0.03221   0.02153  -0.0706   0.5822   1.0000
   4.750   0.8481   0.03247   0.02171  -0.0702   0.5716   1.0000
   5.000   0.8612   0.03411   0.02345  -0.0688   0.5583   1.0000
   5.250   0.8757   0.03573   0.02514  -0.0676   0.5470   1.0000
   5.500   0.9066   0.03612   0.02548  -0.0673   0.5388   1.0000
   5.750   0.9094   0.03875   0.02828  -0.0655   0.5279   1.0000
   6.000   0.9431   0.03904   0.02854  -0.0655   0.5217   1.0000
   6.250   0.9278   0.04350   0.03322  -0.0633   0.5127   1.0000
   6.500   0.9475   0.04510   0.03489  -0.0628   0.5072   1.0000
   6.750   0.9289   0.05031   0.04023  -0.0612   0.5012   1.0000
   7.000   0.8487   0.06169   0.05162  -0.0600   0.4956   1.0000
   7.250   0.8236   0.06821   0.05815  -0.0605   0.4931   1.0000
   7.500   0.7864   0.07598   0.06591  -0.0618   0.4967   1.0000
   7.750   0.7769   0.08113   0.07109  -0.0628   0.5007   1.0000
   8.000   0.7794   0.08525   0.07527  -0.0636   0.5030   1.0000
  11.750   1.3487   0.05328   0.04506  -0.0278   0.2594   1.0000
  12.000   1.2999   0.05900   0.05108  -0.0232   0.2562   1.0000
  12.250   1.2264   0.07012   0.06240  -0.0227   0.2614   1.0000
  12.500   1.3123   0.05797   0.04963  -0.0162   0.2005   1.0000
  12.750   1.2834   0.06296   0.05480  -0.0146   0.1929   1.0000
  13.000   1.2758   0.06579   0.05762  -0.0133   0.1806   1.0000
  13.250   1.2350   0.07376   0.06584  -0.0144   0.1788   1.0000
  13.500   1.1558   0.08971   0.08205  -0.0207   0.1857   1.0000
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