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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 200,000
Max Cl/Cd: 81.39 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe529-il-200000.txt
Download as CSV file: xf-goe529-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2433   0.10115   0.09789  -0.0361   1.0000   0.0398
  -8.500  -0.2506   0.09967   0.09650  -0.0349   1.0000   0.0411
  -8.250  -0.2677   0.09934   0.09629  -0.0317   1.0000   0.0416
  -8.000  -0.2553   0.09650   0.09348  -0.0452   0.9883   0.0426
  -7.750  -0.2343   0.09022   0.08720  -0.0528   0.9801   0.0432
  -7.500  -0.2107   0.08574   0.08271  -0.0509   0.9778   0.0442
  -7.250  -0.1834   0.08198   0.07893  -0.0545   0.9720   0.0468
  -7.000  -0.1570   0.07767   0.07460  -0.0625   0.9606   0.0503
  -6.750  -0.1082   0.07119   0.06795  -0.0890   0.9443   0.0531
  -6.500  -0.0942   0.06639   0.06320  -0.0859   0.9377   0.0544
  -6.250  -0.0686   0.06321   0.05998  -0.0874   0.9277   0.0563
  -6.000  -0.0414   0.05975   0.05645  -0.0922   0.9128   0.0600
  -5.750  -0.0073   0.05423   0.05055  -0.1061   0.8904   0.0654
  -5.500   0.0063   0.05132   0.04766  -0.1042   0.8751   0.0668
  -5.250   0.0234   0.04914   0.04539  -0.1037   0.8587   0.0688
  -5.000   0.0433   0.04672   0.04283  -0.1049   0.8432   0.0723
  -4.750   0.0730   0.04238   0.03797  -0.1109   0.8291   0.0793
  -4.500   0.0891   0.04031   0.03594  -0.1097   0.8177   0.0814
  -4.250   0.1095   0.03851   0.03403  -0.1095   0.8068   0.0849
  -4.000   0.1384   0.03547   0.03044  -0.1123   0.7959   0.0940
  -3.750   0.1585   0.03329   0.02825  -0.1119   0.7872   0.0959
  -3.500   0.1808   0.03178   0.02665  -0.1116   0.7779   0.1002
  -3.250   0.2066   0.02970   0.02422  -0.1123   0.7695   0.1106
  -3.000   0.2377   0.02418   0.01779  -0.1123   0.7626   0.0769
  -2.750   0.2627   0.02031   0.01331  -0.1119   0.7557   0.0680
  -2.500   0.2888   0.01922   0.01198  -0.1115   0.7480   0.0694
  -2.250   0.3156   0.01790   0.01031  -0.1110   0.7411   0.0693
  -2.000   0.3425   0.01686   0.00900  -0.1105   0.7338   0.0695
  -1.750   0.3696   0.01613   0.00807  -0.1101   0.7273   0.0708
  -1.500   0.3963   0.01552   0.00734  -0.1096   0.7197   0.0729
  -1.250   0.4238   0.01516   0.00681  -0.1092   0.7135   0.0768
  -1.000   0.4497   0.01454   0.00616  -0.1087   0.7060   0.0808
  -0.750   0.4768   0.01416   0.00574  -0.1084   0.6999   0.0868
  -0.500   0.5023   0.01377   0.00538  -0.1078   0.6922   0.0966
  -0.250   0.5291   0.01349   0.00510  -0.1073   0.6857   0.1209
   0.000   0.5545   0.01327   0.00502  -0.1069   0.6782   0.1574
   0.250   0.5809   0.01309   0.00490  -0.1065   0.6714   0.1941
   0.500   0.6054   0.01279   0.00489  -0.1059   0.6638   0.2697
   0.750   0.6541   0.01118   0.00480  -0.1101   0.6563   1.0000
   1.000   0.6793   0.01135   0.00484  -0.1095   0.6484   1.0000
   1.250   0.7055   0.01151   0.00483  -0.1090   0.6409   1.0000
   1.500   0.7305   0.01168   0.00493  -0.1083   0.6325   1.0000
   1.750   0.7568   0.01185   0.00495  -0.1078   0.6249   1.0000
   2.000   0.7813   0.01201   0.00507  -0.1071   0.6157   1.0000
   2.250   0.8078   0.01218   0.00509  -0.1067   0.6079   1.0000
   2.500   0.8320   0.01231   0.00522  -0.1059   0.5981   1.0000
   2.750   0.8577   0.01248   0.00531  -0.1054   0.5901   1.0000
   3.000   0.8828   0.01262   0.00541  -0.1048   0.5814   1.0000
   3.250   0.9078   0.01278   0.00553  -0.1042   0.5728   1.0000
   3.500   0.9333   0.01290   0.00559  -0.1036   0.5642   1.0000
   3.750   0.9576   0.01302   0.00573  -0.1029   0.5544   1.0000
   4.000   0.9831   0.01314   0.00578  -0.1023   0.5462   1.0000
   4.250   1.0074   0.01326   0.00593  -0.1016   0.5365   1.0000
   4.500   1.0321   0.01341   0.00608  -0.1010   0.5280   1.0000
   4.750   1.0571   0.01354   0.00618  -0.1004   0.5194   1.0000
   5.000   1.0812   0.01371   0.00637  -0.0997   0.5098   1.0000
   5.250   1.1062   0.01388   0.00652  -0.0991   0.5018   1.0000
   5.500   1.1301   0.01407   0.00675  -0.0984   0.4924   1.0000
   5.750   1.1543   0.01429   0.00697  -0.0978   0.4836   1.0000
   6.000   1.1787   0.01451   0.00718  -0.0972   0.4750   1.0000
   6.250   1.2021   0.01477   0.00750  -0.0964   0.4655   1.0000
   6.500   1.2265   0.01507   0.00777  -0.0958   0.4576   1.0000
   6.750   1.2496   0.01536   0.00812  -0.0951   0.4486   1.0000
   7.000   1.2729   0.01569   0.00849  -0.0943   0.4396   1.0000
   7.250   1.2955   0.01600   0.00877  -0.0935   0.4289   1.0000
   7.500   1.3159   0.01628   0.00905  -0.0922   0.4155   1.0000
   7.750   1.3353   0.01656   0.00938  -0.0908   0.4017   1.0000
   8.000   1.3543   0.01686   0.00975  -0.0893   0.3878   1.0000
   8.250   1.3732   0.01719   0.01013  -0.0879   0.3748   1.0000
   8.500   1.3913   0.01752   0.01053  -0.0863   0.3610   1.0000
   8.750   1.4084   0.01789   0.01094  -0.0846   0.3464   1.0000
   9.000   1.4242   0.01829   0.01140  -0.0827   0.3310   1.0000
   9.250   1.4381   0.01875   0.01189  -0.0805   0.3141   1.0000
   9.500   1.4492   0.01930   0.01244  -0.0779   0.2932   1.0000
   9.750   1.4525   0.02006   0.01311  -0.0741   0.2671   1.0000
  10.000   1.4532   0.02105   0.01399  -0.0702   0.2381   1.0000
  10.250   1.4502   0.02238   0.01517  -0.0661   0.2024   1.0000
  10.500   1.4373   0.02448   0.01694  -0.0615   0.1480   1.0000
  10.750   1.4220   0.02710   0.01927  -0.0574   0.1153   1.0000
  11.000   1.4064   0.03010   0.02204  -0.0540   0.0686   1.0000
  11.250   1.3892   0.03354   0.02529  -0.0512   0.0494   1.0000
  11.500   1.3813   0.03649   0.02828  -0.0493   0.0412   1.0000
  11.750   1.3760   0.03939   0.03126  -0.0480   0.0371   1.0000
  12.000   1.3745   0.04206   0.03405  -0.0470   0.0342   1.0000
  12.250   1.3695   0.04520   0.03728  -0.0462   0.0322   1.0000
  12.500   1.3620   0.04874   0.04093  -0.0457   0.0310   1.0000
  12.750   1.3562   0.05223   0.04454  -0.0453   0.0299   1.0000
  13.000   1.3522   0.05557   0.04802  -0.0450   0.0293   1.0000
  13.250   1.3475   0.05912   0.05169  -0.0449   0.0284   1.0000
  13.500   1.3429   0.06274   0.05542  -0.0450   0.0277   1.0000
  13.750   1.3387   0.06639   0.05917  -0.0451   0.0271   1.0000
  14.000   1.3351   0.07002   0.06289  -0.0453   0.0263   1.0000
  14.250   1.3321   0.07364   0.06658  -0.0456   0.0256   1.0000
  14.500   1.3290   0.07718   0.07016  -0.0457   0.0249   1.0000
  14.750   1.3295   0.07996   0.07293  -0.0449   0.0241   1.0000
  15.000   1.3340   0.08267   0.07576  -0.0450   0.0235   1.0000
  15.250   1.3405   0.08493   0.07812  -0.0445   0.0231   1.0000
  15.500   1.3483   0.08704   0.08032  -0.0439   0.0226   1.0000
  15.750   1.3571   0.08907   0.08245  -0.0433   0.0222   1.0000
  16.000   1.3657   0.09123   0.08474  -0.0426   0.0219   1.0000
  16.250   1.3735   0.09359   0.08727  -0.0422   0.0218   1.0000
  16.500   1.3790   0.09642   0.09026  -0.0420   0.0216   1.0000
  16.750   1.3816   0.09977   0.09380  -0.0423   0.0214   1.0000
  17.000   1.3812   0.10361   0.09782  -0.0431   0.0211   1.0000
  17.250   1.3791   0.10773   0.10212  -0.0443   0.0209   1.0000
  17.500   1.3753   0.11216   0.10673  -0.0457   0.0207   1.0000
  17.750   1.3718   0.11653   0.11125  -0.0474   0.0203   1.0000
  18.000   1.3643   0.12180   0.11672  -0.0497   0.0202   1.0000
  18.250   1.3519   0.12813   0.12330  -0.0528   0.0204   1.0000
  18.500   1.3359   0.13538   0.13080  -0.0568   0.0205   1.0000
  18.750   1.3158   0.14379   0.13950  -0.0618   0.0209   1.0000
  19.000   1.2945   0.15283   0.14879  -0.0675   0.0212   1.0000
  19.250   1.2727   0.16246   0.15864  -0.0738   0.0216   1.0000
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