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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 100,000
Max Cl/Cd: 23.83 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe09k-il-100000-n5.txt
Download as CSV file: xf-goe09k-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 9K AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5890   0.09910   0.09416   0.0055   1.0000   0.0295
  -7.750  -0.5882   0.09605   0.09117   0.0029   1.0000   0.0307
  -7.500  -0.5858   0.09282   0.08801  -0.0003   1.0000   0.0311
  -7.250  -0.5786   0.08914   0.08435  -0.0051   1.0000   0.0314
  -7.000  -0.5682   0.08525   0.08045  -0.0105   1.0000   0.0316
  -6.750  -0.5548   0.08118   0.07631  -0.0156   1.0000   0.0317
  -6.500  -0.5548   0.07661   0.07186  -0.0104   1.0000   0.0345
  -6.250  -0.5411   0.07251   0.06771  -0.0143   1.0000   0.0376
  -6.000  -0.5171   0.06853   0.06350  -0.0218   1.0000   0.0391
  -5.750  -0.5114   0.06384   0.05890  -0.0203   1.0000   0.0415
  -5.500  -0.4923   0.06006   0.05496  -0.0230   1.0000   0.0457
  -5.250  -0.4712   0.05561   0.05028  -0.0261   1.0000   0.0488
  -5.000  -0.4571   0.05171   0.04636  -0.0261   1.0000   0.0520
  -4.500  -0.4142   0.04413   0.03832  -0.0285   1.0000   0.0620
  -4.250  -0.3912   0.04061   0.03449  -0.0293   1.0000   0.0693
  -4.000  -0.3682   0.03736   0.03097  -0.0293   1.0000   0.0728
  -3.750  -0.3350   0.03214   0.02520  -0.0281   1.0000   0.0245
  -3.500  -0.3074   0.02908   0.02161  -0.0271   1.0000   0.0186
  -3.250  -0.2824   0.02593   0.01801  -0.0263   1.0000   0.0165
  -3.000  -0.2549   0.02326   0.01470  -0.0250   1.0000   0.0146
  -2.750  -0.2288   0.02129   0.01227  -0.0239   1.0000   0.0141
  -2.500  -0.2039   0.01893   0.00963  -0.0231   1.0000   0.0157
  -2.250  -0.1783   0.01721   0.00767  -0.0220   1.0000   0.0173
  -2.000  -0.1536   0.01565   0.00589  -0.0209   1.0000   0.0183
  -1.750  -0.1298   0.01433   0.00439  -0.0197   1.0000   0.0227
  -1.500  -0.1052   0.01339   0.00326  -0.0187   1.0000   0.0324
  -1.250  -0.0608   0.00956   0.00231  -0.0219   1.0000   1.0000
  -1.000  -0.0369   0.00955   0.00185  -0.0210   1.0000   1.0000
  -0.750  -0.0129   0.00955   0.00158  -0.0202   1.0000   1.0000
  -0.500   0.0109   0.00956   0.00140  -0.0194   1.0000   1.0000
  -0.250   0.0347   0.00959   0.00128  -0.0187   1.0000   1.0000
   0.000   0.0585   0.00962   0.00121  -0.0180   1.0000   1.0000
   0.250   0.0822   0.00967   0.00121  -0.0173   1.0000   1.0000
   0.500   0.1059   0.00972   0.00127  -0.0165   1.0000   1.0000
   0.750   0.1294   0.00979   0.00139  -0.0158   1.0000   1.0000
   1.000   0.1530   0.00987   0.00156  -0.0151   1.0000   1.0000
   1.250   0.1764   0.00996   0.00178  -0.0143   1.0000   1.0000
   1.500   0.1998   0.01007   0.00207  -0.0136   1.0000   1.0000
   1.750   0.2232   0.01019   0.00253  -0.0128   1.0000   1.0000
   2.000   0.2464   0.01034   0.00304  -0.0120   1.0000   1.0000
   2.250   0.3534   0.01530   0.00500  -0.0264   0.0198   1.0000
   2.500   0.3765   0.01659   0.00649  -0.0250   0.0177   1.0000
   2.750   0.4001   0.01825   0.00821  -0.0238   0.0151   1.0000
   3.000   0.4256   0.02024   0.01041  -0.0227   0.0139   1.0000
   3.250   0.4520   0.02257   0.01305  -0.0216   0.0141   1.0000
   3.500   0.4777   0.02510   0.01598  -0.0205   0.0147   1.0000
   3.750   0.5054   0.02745   0.01898  -0.0187   0.0168   1.0000
   4.000   0.5294   0.03073   0.02273  -0.0173   0.0191   1.0000
   4.250   0.5560   0.03378   0.02632  -0.0155   0.0252   1.0000
   5.750   0.6762   0.05826   0.05266  -0.0111   0.0489   1.0000
   6.250   0.7049   0.06617   0.06111  -0.0127   0.0409   1.0000
   6.500   0.7122   0.07175   0.06663  -0.0125   0.0395   1.0000
   6.750   0.7263   0.07544   0.07069  -0.0169   0.0373   1.0000
   7.000   0.7342   0.07991   0.07525  -0.0193   0.0352   1.0000
   7.250   0.7400   0.08417   0.07953  -0.0205   0.0335   1.0000
   7.500   0.7434   0.08947   0.08475  -0.0181   0.0322   1.0000
   7.750   0.7477   0.09375   0.08910  -0.0215   0.0321   1.0000
   8.000   0.7492   0.09804   0.09341  -0.0256   0.0319   1.0000
   8.250   0.7475   0.10210   0.09743  -0.0294   0.0318   1.0000
   8.500   0.7464   0.10603   0.10131  -0.0330   0.0317   1.0000
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