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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 200,000
Max Cl/Cd: 47.1 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe10k-il-200000.txt
Download as CSV file: xf-goe10k-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 10K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5301   0.09049   0.08699  -0.0111   1.0000   0.0238
  -7.500  -0.5321   0.08759   0.08415  -0.0117   1.0000   0.0240
  -7.250  -0.5321   0.08422   0.08083  -0.0135   1.0000   0.0253
  -7.000  -0.5282   0.08060   0.07723  -0.0161   1.0000   0.0256
  -6.750  -0.5195   0.07668   0.07330  -0.0211   1.0000   0.0271
  -6.500  -0.5075   0.07262   0.06919  -0.0256   1.0000   0.0275
  -6.250  -0.4918   0.06860   0.06505  -0.0298   1.0000   0.0278
  -6.000  -0.4906   0.06328   0.05975  -0.0293   1.0000   0.0289
  -5.750  -0.4844   0.06023   0.05671  -0.0280   1.0000   0.0307
  -5.500  -0.4713   0.05660   0.05300  -0.0290   1.0000   0.0330
  -5.250  -0.4446   0.05249   0.04848  -0.0325   1.0000   0.0366
  -5.000  -0.4340   0.04784   0.04377  -0.0323   1.0000   0.0376
  -4.750  -0.4222   0.04489   0.04083  -0.0313   1.0000   0.0405
  -4.500  -0.3984   0.04140   0.03681  -0.0318   1.0000   0.0455
  -4.250  -0.3861   0.03794   0.03344  -0.0309   1.0000   0.0482
  -4.000  -0.3623   0.03573   0.03055  -0.0301   1.0000   0.0560
  -3.750  -0.3472   0.03194   0.02691  -0.0294   1.0000   0.0590
  -3.500  -0.3263   0.02928   0.02388  -0.0284   1.0000   0.0669
  -3.250  -0.3051   0.02692   0.02120  -0.0273   1.0000   0.0758
  -3.000  -0.2847   0.02476   0.01891  -0.0263   1.0000   0.0883
  -2.750  -0.2492   0.01927   0.01231  -0.0234   1.0000   0.0339
  -2.500  -0.2215   0.01689   0.00936  -0.0216   1.0000   0.0275
  -2.250  -0.1954   0.01489   0.00704  -0.0205   1.0000   0.0271
  -2.000  -0.1707   0.01331   0.00537  -0.0195   1.0000   0.0308
  -1.750  -0.1470   0.01241   0.00438  -0.0183   1.0000   0.0366
  -1.500  -0.1238   0.01130   0.00346  -0.0171   1.0000   0.0850
  -1.250  -0.0651   0.00811   0.00309  -0.0240   1.0000   1.0000
  -1.000  -0.0430   0.00817   0.00293  -0.0229   1.0000   1.0000
  -0.750  -0.0209   0.00824   0.00282  -0.0219   1.0000   1.0000
  -0.500   0.0012   0.00833   0.00274  -0.0208   1.0000   1.0000
  -0.250   0.0232   0.00843   0.00273  -0.0199   1.0000   1.0000
   0.000   0.0452   0.00855   0.00276  -0.0189   1.0000   1.0000
   0.250   0.0672   0.00868   0.00281  -0.0180   1.0000   1.0000
   0.500   0.0892   0.00882   0.00290  -0.0171   1.0000   1.0000
   0.750   0.1112   0.00897   0.00303  -0.0162   1.0000   1.0000
   1.000   0.1331   0.00914   0.00320  -0.0153   1.0000   1.0000
   1.250   0.1549   0.00932   0.00340  -0.0144   1.0000   1.0000
   1.500   0.1766   0.00952   0.00364  -0.0136   1.0000   1.0000
   1.750   0.2046   0.00976   0.00394  -0.0142   0.9982   1.0000
   2.000   0.2735   0.00997   0.00437  -0.0231   0.9839   1.0000
   2.250   0.3648   0.00939   0.00418  -0.0357   0.9557   1.0000
   2.500   0.4677   0.00993   0.00278  -0.0479   0.3329   1.0000
   2.750   0.4751   0.01246   0.00392  -0.0442   0.0406   1.0000
   3.000   0.4953   0.01353   0.00498  -0.0423   0.0292   1.0000
   3.250   0.5162   0.01489   0.00644  -0.0403   0.0267   1.0000
   3.500   0.5396   0.01643   0.00810  -0.0388   0.0241   1.0000
   3.750   0.5659   0.01866   0.01057  -0.0374   0.0244   1.0000
   4.000   0.5926   0.02166   0.01392  -0.0360   0.0279   1.0000
   4.250   0.6321   0.02807   0.02154  -0.0314   0.0903   1.0000
   4.500   0.6511   0.03071   0.02449  -0.0295   0.0800   1.0000
   5.250   0.7012   0.03918   0.03384  -0.0237   0.0532   1.0000
   5.500   0.7166   0.04219   0.03700  -0.0223   0.0483   1.0000
   5.750   0.6916   0.03203   0.02718  -0.0183   0.0464   1.0000
   6.000   0.7028   0.03499   0.03087  -0.0155   0.0413   1.0000
   6.250   0.7534   0.05578   0.05083  -0.0192   0.0379   1.0000
   6.500   0.7633   0.05721   0.05315  -0.0163   0.0347   1.0000
   6.750   0.7721   0.06095   0.05705  -0.0155   0.0323   1.0000
   7.000   0.7789   0.06448   0.06062  -0.0147   0.0307   1.0000
   7.250   0.7808   0.07124   0.06723  -0.0144   0.0296   1.0000
   7.500   0.7824   0.07486   0.07112  -0.0138   0.0295   1.0000
   7.750   0.7822   0.07885   0.07532  -0.0143   0.0292   1.0000
   8.000   0.7803   0.08320   0.07980  -0.0160   0.0289   1.0000
   8.250   0.7746   0.08742   0.08407  -0.0177   0.0287   1.0000
   8.500   0.7672   0.09177   0.08843  -0.0201   0.0286   1.0000
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