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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.39 at α=0.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe09k-il-1000000-n5.txt
Download as CSV file: xf-goe09k-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5875   0.09389   0.09227   0.0064   1.0000   0.0011
  -7.750  -0.5864   0.09061   0.08901   0.0051   1.0000   0.0012
  -7.500  -0.5867   0.08746   0.08589   0.0039   1.0000   0.0013
  -7.250  -0.5829   0.08382   0.08226   0.0012   1.0000   0.0013
  -7.000  -0.5755   0.07985   0.07829  -0.0023   1.0000   0.0012
  -6.750  -0.5658   0.07559   0.07402  -0.0062   1.0000   0.0016
  -6.500  -0.5543   0.07135   0.06977  -0.0099   1.0000   0.0014
  -6.250  -0.5373   0.06659   0.06498  -0.0140   1.0000   0.0019
  -6.000  -0.5184   0.06180   0.06013  -0.0181   1.0000   0.0019
  -5.750  -0.5002   0.05720   0.05545  -0.0210   1.0000   0.0019
  -5.500  -0.4813   0.05282   0.05099  -0.0231   1.0000   0.0020
  -5.250  -0.4617   0.04849   0.04655  -0.0247   1.0000   0.0020
  -5.000  -0.4449   0.04396   0.04190  -0.0260   1.0000   0.0020
  -4.750  -0.4261   0.04027   0.03808  -0.0266   1.0000   0.0021
  -4.500  -0.4048   0.03655   0.03420  -0.0269   1.0000   0.0022
  -4.250  -0.3830   0.03297   0.03045  -0.0267   1.0000   0.0023
  -4.000  -0.3606   0.02958   0.02685  -0.0262   1.0000   0.0024
  -3.750  -0.3378   0.02630   0.02334  -0.0252   1.0000   0.0026
  -3.500  -0.3145   0.02320   0.02000  -0.0241   1.0000   0.0028
  -3.250  -0.2833   0.01998   0.01646  -0.0236   0.9993   0.0032
  -3.000  -0.2512   0.01714   0.01329  -0.0237   0.9981   0.0033
  -2.500  -0.1906   0.01165   0.00709  -0.0238   0.9959   0.0018
  -2.250  -0.1612   0.00972   0.00487  -0.0235   0.9951   0.0015
  -2.000  -0.1333   0.00825   0.00318  -0.0230   0.9939   0.0014
  -1.750  -0.1047   0.00729   0.00202  -0.0229   0.9924   0.0014
  -1.500  -0.0750   0.00672   0.00132  -0.0232   0.9908   0.0018
  -1.250  -0.0434   0.00640   0.00094  -0.0241   0.9891   0.0054
  -1.000  -0.0105   0.00595   0.00069  -0.0254   0.9871   0.0818
  -0.750   0.0164   0.00504   0.00059  -0.0258   0.9826   0.3605
  -0.500   0.0501   0.00451   0.00051  -0.0276   0.9783   0.5199
  -0.250   0.0789   0.00397   0.00044  -0.0280   0.9692   0.6809
   0.000   0.1053   0.00334   0.00042  -0.0276   0.9584   0.8635
   0.250   0.1963   0.00312   0.00034  -0.0421   0.9047   0.9997
   0.500   0.2187   0.00345   0.00032  -0.0407   0.8087   1.0000
   0.750   0.2358   0.00403   0.00037  -0.0383   0.6639   1.0000
   1.000   0.2511   0.00518   0.00055  -0.0360   0.3766   1.0000
   1.250   0.2686   0.00647   0.00081  -0.0344   0.0528   1.0000
   1.500   0.2926   0.00691   0.00112  -0.0336   0.0040   1.0000
   2.000   0.3411   0.00788   0.00227  -0.0317   0.0016   1.0000
   2.250   0.3639   0.00877   0.00331  -0.0304   0.0016   1.0000
   2.500   0.3868   0.01001   0.00471  -0.0288   0.0017   1.0000
   2.750   0.4106   0.01162   0.00651  -0.0274   0.0019   1.0000
   4.500   0.5724   0.03046   0.02733  -0.0160   0.0020   1.0000
   4.750   0.5965   0.03433   0.03145  -0.0140   0.0015   1.0000
   5.000   0.6167   0.03814   0.03549  -0.0129   0.0013   1.0000
   5.250   0.6359   0.04214   0.03969  -0.0121   0.0013   1.0000
   5.500   0.6540   0.04629   0.04402  -0.0117   0.0012   1.0000
   5.750   0.6688   0.05025   0.04812  -0.0119   0.0011   1.0000
   6.000   0.6814   0.05527   0.05329  -0.0123   0.0011   1.0000
   6.250   0.6956   0.05985   0.05799  -0.0131   0.0011   1.0000
   6.500   0.7084   0.06458   0.06282  -0.0144   0.0011   1.0000
   6.750   0.7193   0.06940   0.06772  -0.0161   0.0011   1.0000
   7.000   0.7280   0.07428   0.07267  -0.0184   0.0011   1.0000
   7.250   0.7349   0.07902   0.07745  -0.0212   0.0011   1.0000
   7.500   0.7395   0.08357   0.08202  -0.0242   0.0011   1.0000
   7.750   0.7411   0.08800   0.08647  -0.0275   0.0011   1.0000
   8.000   0.7359   0.09202   0.09047  -0.0304   0.0011   1.0000
   8.250   0.7344   0.09611   0.09454  -0.0330   0.0011   1.0000
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