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GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 510 AIRFOIL (goe510-il)
Reynolds number: 100,000
Max Cl/Cd: 48.09 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe510-il-100000-n5.txt
Download as CSV file: xf-goe510-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 510 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1800   0.10022   0.09523  -0.0719   0.9482   0.0901
  -8.000  -0.1877   0.09713   0.09215  -0.0763   0.9387   0.0904
  -7.750  -0.1811   0.09314   0.08817  -0.0777   0.9318   0.0908
  -7.500  -0.1515   0.08913   0.08416  -0.0777   0.9300   0.0918
  -7.250  -0.1445   0.08641   0.08144  -0.0776   0.9215   0.0924
  -7.000  -0.1305   0.08320   0.07821  -0.0793   0.9150   0.0934
  -6.500  -0.1516   0.06941   0.06409  -0.0869   0.8897   0.0671
  -6.250  -0.1329   0.06621   0.06086  -0.0882   0.8838   0.0664
  -6.000  -0.1247   0.06331   0.05790  -0.0877   0.8736   0.0656
  -5.750  -0.1070   0.05922   0.05368  -0.0898   0.8673   0.0646
  -5.500  -0.1011   0.05571   0.05003  -0.0891   0.8561   0.0638
  -5.250  -0.0821   0.05085   0.04493  -0.0912   0.8506   0.0631
  -5.000  -0.0771   0.04702   0.04086  -0.0897   0.8392   0.0632
  -4.750  -0.0592   0.04156   0.03494  -0.0908   0.8342   0.0641
  -4.500  -0.0541   0.03828   0.03126  -0.0881   0.8234   0.0645
  -4.250  -0.0314   0.03483   0.02731  -0.0881   0.8184   0.0645
  -4.000  -0.0180   0.03266   0.02475  -0.0859   0.8089   0.0648
  -3.750   0.0079   0.03047   0.02211  -0.0857   0.8029   0.0654
  -3.500   0.0326   0.02887   0.02008  -0.0851   0.7957   0.0664
  -3.250   0.0566   0.02760   0.01845  -0.0842   0.7873   0.0678
  -3.000   0.0945   0.02613   0.01684  -0.0861   0.7828   0.0693
  -2.750   0.1115   0.02540   0.01598  -0.0839   0.7713   0.0701
  -2.500   0.1517   0.02422   0.01460  -0.0860   0.7658   0.0712
  -2.250   0.1707   0.02362   0.01388  -0.0841   0.7540   0.0722
  -2.000   0.2058   0.02279   0.01289  -0.0852   0.7461   0.0739
  -1.750   0.2325   0.02223   0.01221  -0.0847   0.7355   0.0761
  -1.500   0.2616   0.02172   0.01154  -0.0846   0.7252   0.0780
  -1.250   0.2978   0.02095   0.01074  -0.0860   0.7157   0.0801
  -1.000   0.3213   0.02054   0.01032  -0.0850   0.7033   0.0818
  -0.750   0.3516   0.02013   0.00984  -0.0852   0.6919   0.0840
  -0.500   0.3873   0.01970   0.00931  -0.0865   0.6812   0.0876
  -0.250   0.4119   0.01946   0.00901  -0.0856   0.6682   0.0915
   0.000   0.4391   0.01919   0.00872  -0.0853   0.6553   0.0965
   0.250   0.4694   0.01898   0.00843  -0.0855   0.6428   0.1022
   0.500   0.5016   0.01875   0.00821  -0.0861   0.6305   0.1131
   0.750   0.5270   0.01860   0.00821  -0.0855   0.6170   0.1432
   1.000   0.5514   0.01856   0.00833  -0.0848   0.6038   0.2111
   1.250   0.5764   0.01866   0.00838  -0.0841   0.5912   0.2528
   1.500   0.6009   0.01878   0.00842  -0.0833   0.5788   0.2843
   1.750   0.6207   0.01888   0.00852  -0.0817   0.5660   0.3078
   2.000   0.6425   0.01897   0.00856  -0.0805   0.5542   0.3304
   2.250   0.6658   0.01903   0.00854  -0.0795   0.5435   0.3510
   2.500   0.6831   0.01906   0.00860  -0.0775   0.5324   0.3737
   2.750   0.7021   0.01902   0.00860  -0.0758   0.5227   0.4080
   3.250   0.8996   0.01925   0.00973  -0.1051   0.4938   1.0000
   3.500   0.9146   0.01950   0.00991  -0.1026   0.4851   1.0000
   3.750   0.9322   0.01976   0.01002  -0.1007   0.4778   1.0000
   4.000   0.9479   0.02003   0.01023  -0.0984   0.4704   1.0000
   4.250   0.9645   0.02030   0.01040  -0.0963   0.4634   1.0000
   4.500   0.9819   0.02060   0.01060  -0.0943   0.4569   1.0000
   4.750   0.9971   0.02089   0.01086  -0.0920   0.4502   1.0000
   5.000   1.0159   0.02120   0.01106  -0.0903   0.4443   1.0000
   5.250   1.0316   0.02152   0.01135  -0.0881   0.4383   1.0000
   5.500   1.0464   0.02184   0.01165  -0.0857   0.4322   1.0000
   5.750   1.0662   0.02217   0.01189  -0.0843   0.4270   1.0000
   6.000   1.0804   0.02252   0.01224  -0.0818   0.4214   1.0000
   6.250   1.0939   0.02286   0.01259  -0.0793   0.4155   1.0000
   6.500   1.1127   0.02322   0.01288  -0.0777   0.4105   1.0000
   6.750   1.1297   0.02361   0.01326  -0.0759   0.4056   1.0000
   7.000   1.1414   0.02399   0.01369  -0.0730   0.4000   1.0000
   7.250   1.1576   0.02437   0.01406  -0.0711   0.3948   1.0000
   7.500   1.1779   0.02478   0.01441  -0.0699   0.3901   1.0000
   7.750   1.1865   0.02522   0.01496  -0.0666   0.3846   1.0000
   8.000   1.2007   0.02566   0.01543  -0.0644   0.3796   1.0000
   8.250   1.2195   0.02606   0.01580  -0.0630   0.3749   1.0000
   8.500   1.2304   0.02657   0.01639  -0.0603   0.3698   1.0000
   8.750   1.2406   0.02708   0.01698  -0.0575   0.3644   1.0000
   9.000   1.2562   0.02754   0.01745  -0.0557   0.3597   1.0000
   9.250   1.2721   0.02803   0.01797  -0.0540   0.3552   1.0000
   9.500   1.2786   0.02868   0.01876  -0.0508   0.3498   1.0000
   9.750   1.2904   0.02923   0.01936  -0.0485   0.3447   1.0000
  10.000   1.3083   0.02967   0.01976  -0.0472   0.3403   1.0000
  10.250   1.3110   0.03049   0.02075  -0.0437   0.3347   1.0000
  10.500   1.3173   0.03115   0.02149  -0.0408   0.3285   1.0000
  10.750   1.3262   0.03170   0.02203  -0.0383   0.3224   1.0000
  11.000   1.3247   0.03269   0.02318  -0.0347   0.3150   1.0000
  11.250   1.3309   0.03329   0.02371  -0.0321   0.3077   1.0000
  11.500   1.3262   0.03459   0.02519  -0.0286   0.2993   1.0000
  11.750   1.3298   0.03546   0.02602  -0.0260   0.2918   1.0000
  12.000   1.3269   0.03698   0.02772  -0.0232   0.2838   1.0000
  12.250   1.3293   0.03813   0.02884  -0.0209   0.2763   1.0000
  12.500   1.3264   0.03990   0.03077  -0.0186   0.2684   1.0000
  12.750   1.3274   0.04137   0.03225  -0.0166   0.2613   1.0000
  13.000   1.3233   0.04347   0.03448  -0.0147   0.2531   1.0000
  13.250   1.3220   0.04536   0.03639  -0.0130   0.2460   1.0000
  13.500   1.3184   0.04772   0.03889  -0.0116   0.2391   1.0000
  13.750   1.3152   0.05009   0.04133  -0.0104   0.2323   1.0000
  14.000   1.3082   0.05299   0.04434  -0.0093   0.2245   1.0000
  14.250   1.3004   0.05609   0.04749  -0.0085   0.2166   1.0000
  14.500   1.2906   0.05966   0.05116  -0.0079   0.2089   1.0000
  14.750   1.2807   0.06333   0.05489  -0.0076   0.2013   1.0000
  15.000   1.2703   0.06731   0.05900  -0.0075   0.1948   1.0000
  15.250   1.2581   0.07163   0.06340  -0.0077   0.1877   1.0000
  15.500   1.2472   0.07593   0.06781  -0.0080   0.1817   1.0000
  15.750   1.2338   0.08074   0.07273  -0.0087   0.1747   1.0000
  16.000   1.2226   0.08531   0.07738  -0.0094   0.1683   1.0000
  16.250   1.2082   0.09050   0.08266  -0.0104   0.1602   1.0000
  16.500   1.1960   0.09541   0.08765  -0.0114   0.1529   1.0000
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