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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 200,000
Max Cl/Cd: 56.41 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe10k-il-200000-n5.txt
Download as CSV file: xf-goe10k-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5331   0.09244   0.08893  -0.0124   1.0000   0.0131
  -7.750  -0.5325   0.08931   0.08582  -0.0122   1.0000   0.0135
  -7.500  -0.5347   0.08631   0.08287  -0.0130   1.0000   0.0135
  -7.250  -0.5323   0.08305   0.07965  -0.0139   1.0000   0.0143
  -7.000  -0.5285   0.07933   0.07594  -0.0164   1.0000   0.0142
  -6.750  -0.5221   0.07571   0.07233  -0.0189   1.0000   0.0155
  -6.500  -0.5144   0.07171   0.06832  -0.0215   1.0000   0.0156
  -6.000  -0.4759   0.06408   0.06046  -0.0296   1.0000   0.0178
  -5.500  -0.4632   0.05394   0.05019  -0.0310   1.0000   0.0190
  -5.250  -0.4527   0.05062   0.04682  -0.0307   1.0000   0.0203
  -5.000  -0.4373   0.04704   0.04310  -0.0310   1.0000   0.0212
  -4.750  -0.4201   0.04332   0.03919  -0.0312   1.0000   0.0224
  -4.500  -0.4015   0.03957   0.03521  -0.0310   1.0000   0.0229
  -4.250  -0.3766   0.03302   0.02812  -0.0298   1.0000   0.0133
  -4.000  -0.3582   0.02979   0.02462  -0.0288   1.0000   0.0107
  -3.750  -0.3347   0.02509   0.01932  -0.0270   1.0000   0.0090
  -3.500  -0.3130   0.02219   0.01598  -0.0257   1.0000   0.0087
  -3.250  -0.2897   0.01952   0.01279  -0.0244   1.0000   0.0085
  -3.000  -0.2650   0.01737   0.01009  -0.0230   1.0000   0.0091
  -2.750  -0.2416   0.01592   0.00841  -0.0221   1.0000   0.0105
  -2.500  -0.2169   0.01446   0.00668  -0.0210   1.0000   0.0112
  -2.250  -0.1930   0.01338   0.00541  -0.0199   1.0000   0.0123
  -2.000  -0.1698   0.01259   0.00454  -0.0189   1.0000   0.0160
  -1.750  -0.1464   0.01189   0.00368  -0.0179   1.0000   0.0208
  -1.500  -0.1167   0.01128   0.00317  -0.0183   0.9981   0.0636
  -1.250  -0.0878   0.01058   0.00298  -0.0192   0.9960   0.1964
  -1.000  -0.0652   0.00925   0.00293  -0.0188   0.9938   0.5695
  -0.750  -0.0162   0.00825   0.00281  -0.0229   0.9989   1.0000
  -0.500   0.0171   0.00836   0.00273  -0.0243   0.9960   1.0000
  -0.250   0.0493   0.00845   0.00271  -0.0255   0.9930   1.0000
   0.000   0.0818   0.00855   0.00271  -0.0268   0.9898   1.0000
   0.250   0.1157   0.00867   0.00278  -0.0283   0.9870   1.0000
   0.500   0.1484   0.00872   0.00281  -0.0296   0.9820   1.0000
   0.750   0.1890   0.00873   0.00283  -0.0325   0.9751   1.0000
   1.000   0.2318   0.00868   0.00283  -0.0358   0.9670   1.0000
   1.250   0.2702   0.00856   0.00278  -0.0380   0.9557   1.0000
   1.500   0.3101   0.00837   0.00272  -0.0403   0.9417   1.0000
   1.750   0.3596   0.00801   0.00252  -0.0444   0.9148   1.0000
   2.000   0.4310   0.00764   0.00228  -0.0529   0.8295   1.0000
   2.250   0.4476   0.00936   0.00229  -0.0496   0.4197   1.0000
   2.500   0.4544   0.01144   0.00283  -0.0462   0.0843   1.0000
   2.750   0.4750   0.01229   0.00343  -0.0447   0.0221   1.0000
   3.000   0.4970   0.01303   0.00430  -0.0433   0.0149   1.0000
   3.250   0.5181   0.01403   0.00543  -0.0417   0.0124   1.0000
   3.500   0.5397   0.01504   0.00653  -0.0403   0.0106   1.0000
   3.750   0.5616   0.01640   0.00803  -0.0388   0.0090   1.0000
   4.000   0.5853   0.01812   0.00998  -0.0374   0.0086   1.0000
   4.250   0.6100   0.02031   0.01252  -0.0360   0.0084   1.0000
   4.500   0.6339   0.02290   0.01555  -0.0343   0.0084   1.0000
   4.750   0.6553   0.02492   0.01791  -0.0329   0.0074   1.0000
   5.000   0.6746   0.02788   0.02131  -0.0310   0.0069   1.0000
   5.500   0.7106   0.03646   0.03096  -0.0252   0.0086   1.0000
   5.750   0.7243   0.03966   0.03441  -0.0235   0.0101   1.0000
   6.250   0.7429   0.05147   0.04682  -0.0189   0.0194   1.0000
   6.500   0.7449   0.05763   0.05323  -0.0175   0.0189   1.0000
   6.750   0.7540   0.06137   0.05722  -0.0162   0.0188   1.0000
   7.000   0.7694   0.06397   0.06011  -0.0153   0.0180   1.0000
   7.250   0.7780   0.06824   0.06459  -0.0152   0.0169   1.0000
   7.500   0.7813   0.07261   0.06909  -0.0155   0.0165   1.0000
   7.750   0.7815   0.07719   0.07375  -0.0164   0.0162   1.0000
   8.000   0.7793   0.08169   0.07831  -0.0177   0.0160   1.0000
   8.250   0.7727   0.08584   0.08248  -0.0188   0.0159   1.0000
   8.500   0.7654   0.09044   0.08709  -0.0219   0.0159   1.0000
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