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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 50,000
Max Cl/Cd: 20.04 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe534-il-50000.txt
Download as CSV file: xf-goe534-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2241   0.12337   0.11598  -0.0201   1.0000   0.2160
 -10.000  -0.2298   0.12285   0.11555  -0.0210   1.0000   0.2224
  -9.750  -0.2440   0.12290   0.11574  -0.0221   1.0000   0.2248
  -9.500  -0.2107   0.11588   0.10871  -0.0207   1.0000   0.2305
  -9.250  -0.2073   0.11401   0.10691  -0.0205   1.0000   0.2382
  -9.000  -0.2379   0.11689   0.10998  -0.0216   1.0000   0.2424
  -8.750  -0.1999   0.10889   0.10198  -0.0201   1.0000   0.2481
  -8.500  -0.1945   0.10669   0.09987  -0.0195   1.0000   0.2553
  -8.250  -0.2237   0.10888   0.10227  -0.0194   1.0000   0.2608
  -8.000  -0.2004   0.10304   0.09647  -0.0185   1.0000   0.2648
  -7.750  -0.1898   0.10022   0.09374  -0.0172   1.0000   0.2724
  -7.500  -0.2143   0.10132   0.09506  -0.0155   1.0000   0.2790
  -7.250  -0.2593   0.10415   0.09818  -0.0112   1.0000   0.2803
  -7.000  -0.2087   0.09614   0.09013  -0.0109   1.0000   0.2896
  -6.750  -0.2321   0.09662   0.09079  -0.0066   1.0000   0.2947
  -6.500  -0.2692   0.09828   0.09265  -0.0016   1.0000   0.2974
  -6.250  -0.3122   0.10032   0.09488   0.0032   1.0000   0.2987
  -6.000  -0.3555   0.10255   0.09728   0.0047   1.0000   0.2999
  -5.750  -0.3183   0.09611   0.09087   0.0086   1.0000   0.3073
  -5.500  -0.3298   0.09562   0.09048   0.0094   0.9975   0.3146
  -4.750  -0.2269   0.08395   0.07873  -0.0133   0.9513   0.3627
  -4.500  -0.1964   0.08058   0.07533  -0.0187   0.9354   0.3821
  -4.250  -0.1673   0.07724   0.07196  -0.0222   0.9196   0.4023
  -4.000  -0.1398   0.07403   0.06873  -0.0243   0.9042   0.4233
  -3.750  -0.0905   0.06044   0.05428  -0.0644   0.8864   0.2801
  -3.500  -0.0598   0.05799   0.05184  -0.0655   0.8725   0.2846
  -3.250   0.0052   0.05182   0.04520  -0.0789   0.8619   0.2752
  -3.000   0.0387   0.04865   0.04173  -0.0839   0.8464   0.2752
  -2.750   0.0808   0.04545   0.03815  -0.0896   0.8331   0.2752
  -2.500   0.1428   0.04172   0.03383  -0.0976   0.8229   0.2814
  -2.250   0.1658   0.04116   0.03325  -0.0972   0.8074   0.2855
  -2.000   0.2016   0.03995   0.03182  -0.0989   0.7943   0.2922
  -1.750   0.2485   0.03837   0.02997  -0.1017   0.7830   0.3045
  -1.500   0.2690   0.03824   0.02974  -0.1008   0.7678   0.3147
  -1.250   0.3032   0.03756   0.02897  -0.1013   0.7555   0.3292
  -1.000   0.3391   0.03691   0.02823  -0.1016   0.7432   0.3523
  -0.750   0.3583   0.03711   0.02834  -0.1003   0.7285   0.3799
  -0.500   0.3939   0.03656   0.02786  -0.0996   0.7179   0.4219
  -0.250   0.4130   0.03677   0.02809  -0.0976   0.7039   0.4592
   0.000   0.4286   0.03718   0.02857  -0.0953   0.6901   0.4910
   0.250   0.4682   0.03627   0.02759  -0.0945   0.6806   0.5380
   0.500   0.4781   0.03709   0.02844  -0.0922   0.6653   0.5708
   0.750   0.4979   0.03722   0.02863  -0.0902   0.6530   0.6101
   1.000   0.5315   0.03639   0.02780  -0.0891   0.6423   0.6539
   1.250   0.5467   0.03713   0.02855  -0.0879   0.6279   0.6827
   1.500   0.5805   0.03657   0.02804  -0.0875   0.6173   0.7218
   1.750   0.6067   0.03634   0.02805  -0.0867   0.6050   0.7689
   2.000   0.6431   0.03666   0.02875  -0.0889   0.5902   1.0000
   2.250   0.6869   0.03682   0.02854  -0.0910   0.5794   1.0000
   2.500   0.7154   0.03771   0.02918  -0.0916   0.5667   1.0000
   2.750   0.7299   0.03960   0.03093  -0.0911   0.5534   1.0000
   3.000   0.7778   0.03881   0.02978  -0.0916   0.5450   1.0000
   3.250   0.7761   0.04184   0.03284  -0.0901   0.5309   1.0000
   3.500   0.8064   0.04236   0.03315  -0.0896   0.5215   1.0000
   3.750   0.8154   0.04454   0.03529  -0.0884   0.5098   1.0000
   4.000   0.8190   0.04736   0.03808  -0.0871   0.4994   1.0000
   4.250   0.8404   0.04852   0.03914  -0.0862   0.4898   1.0000
   4.500   0.8141   0.05403   0.04472  -0.0846   0.4790   1.0000
   4.750   0.8318   0.05565   0.04626  -0.0837   0.4705   1.0000
   5.000   0.7897   0.06282   0.05346  -0.0827   0.4624   1.0000
   5.250   0.7365   0.07133   0.06202  -0.0836   0.4559   1.0000
   5.500   0.8802   0.06115   0.05159  -0.0809   0.4475   1.0000
   5.750   0.6002   0.09413   0.08516  -0.0934   0.5345   1.0000
   6.000   0.6212   0.09578   0.08672  -0.0924   0.5138   1.0000
   6.250   0.6478   0.09703   0.08785  -0.0912   0.4916   1.0000
   6.500   0.6723   0.09989   0.09064  -0.0912   0.4840   1.0000
   6.750   0.7131   0.09798   0.08858  -0.0875   0.4450   1.0000
   7.000   0.7306   0.10203   0.09262  -0.0884   0.4475   1.0000
   7.250   0.6248   0.11424   0.10510  -0.0962   0.5312   1.0000
   7.500   0.6623   0.11912   0.10991  -0.0974   0.5242   1.0000
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