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GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 287 AIRFOIL (goe287-il)
Reynolds number: 200,000
Max Cl/Cd: 80 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe287-il-200000.txt
Download as CSV file: xf-goe287-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 287 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3790   0.11441   0.11123  -0.0053   1.0000   0.0308
  -9.000  -0.3764   0.11214   0.10901  -0.0098   1.0000   0.0311
  -8.750  -0.3721   0.10936   0.10628  -0.0141   1.0000   0.0312
  -8.500  -0.3667   0.10622   0.10319  -0.0181   1.0000   0.0313
  -8.250  -0.3596   0.10276   0.09978  -0.0227   1.0000   0.0314
  -8.000  -0.3475   0.09584   0.09287  -0.0164   1.0000   0.0325
  -7.750  -0.3369   0.09250   0.08955  -0.0169   1.0000   0.0335
  -7.500  -0.3281   0.08932   0.08643  -0.0191   1.0000   0.0345
  -7.250  -0.3185   0.08603   0.08319  -0.0226   1.0000   0.0355
  -7.000  -0.2956   0.08161   0.07874  -0.0301   0.9660   0.0371
  -6.750  -0.2767   0.07772   0.07480  -0.0368   0.9351   0.0390
  -6.500  -0.2482   0.07441   0.07127  -0.0497   0.9035   0.0407
  -6.250  -0.2292   0.07098   0.06764  -0.0539   0.8813   0.0409
  -6.000  -0.2296   0.06517   0.06185  -0.0516   0.8639   0.0419
  -5.750  -0.2221   0.06264   0.05927  -0.0490   0.8464   0.0431
  -5.500  -0.2073   0.05998   0.05649  -0.0493   0.8301   0.0450
  -5.250  -0.1862   0.05678   0.05312  -0.0519   0.8151   0.0475
  -5.000  -0.1376   0.05422   0.04993  -0.0608   0.8011   0.0526
  -4.750  -0.1233   0.04819   0.04385  -0.0622   0.7891   0.0540
  -4.500  -0.1064   0.04559   0.04122  -0.0620   0.7770   0.0556
  -4.250  -0.0845   0.04342   0.03892  -0.0626   0.7663   0.0592
  -4.000  -0.0442   0.04051   0.03532  -0.0666   0.7560   0.0670
  -3.750  -0.0244   0.03724   0.03213  -0.0670   0.7463   0.0689
  -3.500  -0.0006   0.03527   0.03002  -0.0674   0.7382   0.0724
  -3.250   0.0337   0.03309   0.02731  -0.0692   0.7290   0.0820
  -3.000   0.0566   0.03095   0.02520  -0.0696   0.7222   0.0859
  -2.750   0.0883   0.02930   0.02313  -0.0707   0.7145   0.0970
  -2.500   0.1137   0.02748   0.02127  -0.0710   0.7088   0.1019
  -2.250   0.1434   0.02592   0.01946  -0.0719   0.7021   0.1137
  -2.000   0.1718   0.02461   0.01792  -0.0724   0.6960   0.1277
  -1.750   0.1993   0.02336   0.01658  -0.0728   0.6896   0.1442
  -1.000   0.2992   0.01823   0.01002  -0.0719   0.6704   0.0735
  -0.750   0.3294   0.01736   0.00875  -0.0715   0.6653   0.0675
  -0.500   0.3584   0.01663   0.00791  -0.0715   0.6595   0.0676
  -0.250   0.3869   0.01593   0.00716  -0.0716   0.6537   0.0693
   0.000   0.4152   0.01542   0.00654  -0.0714   0.6488   0.0689
   0.250   0.4439   0.01492   0.00608  -0.0715   0.6423   0.0694
   0.500   0.4721   0.01453   0.00567  -0.0714   0.6369   0.0710
   0.750   0.5006   0.01427   0.00541  -0.0715   0.6319   0.0738
   1.000   0.5293   0.01406   0.00522  -0.0716   0.6264   0.0780
   1.250   0.5577   0.01387   0.00500  -0.0717   0.6213   0.0881
   1.500   0.5865   0.01361   0.00486  -0.0718   0.6156   0.1246
   1.750   0.6095   0.01160   0.00475  -0.0707   0.6098   1.0000
   2.000   0.6376   0.01175   0.00473  -0.0706   0.6051   1.0000
   2.250   0.6662   0.01189   0.00484  -0.0708   0.5993   1.0000
   2.500   0.6943   0.01202   0.00490  -0.0708   0.5936   1.0000
   2.750   0.7224   0.01217   0.00497  -0.0708   0.5881   1.0000
   3.000   0.7505   0.01228   0.00509  -0.0709   0.5811   1.0000
   3.250   0.7783   0.01243   0.00513  -0.0708   0.5752   1.0000
   3.500   0.8064   0.01253   0.00529  -0.0710   0.5673   1.0000
   3.750   0.8342   0.01266   0.00535  -0.0709   0.5608   1.0000
   4.000   0.8620   0.01276   0.00552  -0.0710   0.5521   1.0000
   4.250   0.8897   0.01287   0.00559  -0.0709   0.5442   1.0000
   4.500   0.9173   0.01294   0.00571  -0.0708   0.5339   1.0000
   4.750   0.9447   0.01301   0.00583  -0.0708   0.5225   1.0000
   5.000   0.9719   0.01305   0.00591  -0.0706   0.5091   1.0000
   5.250   0.9989   0.01308   0.00597  -0.0705   0.4922   1.0000
   5.500   1.0257   0.01311   0.00601  -0.0703   0.4708   1.0000
   5.750   1.0520   0.01315   0.00604  -0.0701   0.4330   1.0000
   6.000   1.0762   0.01349   0.00611  -0.0697   0.3796   1.0000
   6.500   1.1223   0.01485   0.00708  -0.0690   0.3211   1.0000
   6.750   1.1459   0.01548   0.00764  -0.0686   0.3035   1.0000
   7.000   1.1687   0.01614   0.00823  -0.0683   0.2801   1.0000
   7.250   1.1910   0.01680   0.00881  -0.0679   0.2529   1.0000
   7.500   1.2122   0.01759   0.00944  -0.0673   0.2128   1.0000
   7.750   1.2221   0.01971   0.01074  -0.0658   0.0930   1.0000
   8.000   1.2314   0.02185   0.01252  -0.0639   0.0406   1.0000
   8.250   1.2494   0.02286   0.01372  -0.0628   0.0373   1.0000
   8.500   1.2648   0.02405   0.01509  -0.0614   0.0350   1.0000
   8.750   1.2752   0.02557   0.01679  -0.0596   0.0329   1.0000
   9.000   1.2768   0.02756   0.01897  -0.0570   0.0313   1.0000
   9.250   1.2819   0.02899   0.02050  -0.0546   0.0304   1.0000
   9.500   1.2844   0.03083   0.02247  -0.0526   0.0299   1.0000
   9.750   1.2865   0.03293   0.02467  -0.0510   0.0294   1.0000
  10.000   1.2887   0.03519   0.02702  -0.0496   0.0289   1.0000
  10.250   1.2918   0.03747   0.02938  -0.0483   0.0285   1.0000
  10.500   1.2961   0.03967   0.03166  -0.0470   0.0282   1.0000
  10.750   1.3025   0.04173   0.03380  -0.0455   0.0278   1.0000
  11.000   1.3109   0.04364   0.03575  -0.0440   0.0272   1.0000
  11.250   1.3211   0.04545   0.03758  -0.0425   0.0262   1.0000
  11.500   1.3340   0.04718   0.03933  -0.0409   0.0254   1.0000
  11.750   1.3525   0.04875   0.04097  -0.0391   0.0253   1.0000
  12.000   1.3739   0.05044   0.04279  -0.0374   0.0256   1.0000
  12.250   1.3910   0.05268   0.04532  -0.0358   0.0265   1.0000
  12.500   1.4108   0.05559   0.04853  -0.0341   0.0283   1.0000
  12.750   1.2466   0.05317   0.04651  -0.0227   0.0266   1.0000
  13.000   1.2573   0.05641   0.05002  -0.0210   0.0276   1.0000
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