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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 500,000
Max Cl/Cd: 111.26 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe477-il-500000.txt
Download as CSV file: xf-goe477-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1874   0.08293   0.08045  -0.0860   0.9197   0.0293
  -9.250  -0.1783   0.07886   0.07633  -0.0878   0.9115   0.0299
  -9.000  -0.4180   0.02625   0.02247  -0.1119   0.8762   0.0200
  -8.750  -0.3985   0.02516   0.02129  -0.1115   0.8731   0.0206
  -8.500  -0.3722   0.02536   0.02151  -0.1113   0.8704   0.0214
  -8.250  -0.3553   0.02343   0.01927  -0.1107   0.8674   0.0222
  -8.000  -0.3395   0.02098   0.01636  -0.1099   0.8645   0.0232
  -7.750  -0.3193   0.01943   0.01446  -0.1092   0.8618   0.0239
  -7.500  -0.3004   0.01754   0.01231  -0.1083   0.8590   0.0251
  -7.250  -0.2750   0.01719   0.01192  -0.1080   0.8564   0.0261
  -7.000  -0.2499   0.01666   0.01124  -0.1076   0.8540   0.0274
  -6.750  -0.2241   0.01620   0.01060  -0.1073   0.8518   0.0290
  -6.500  -0.1999   0.01535   0.00961  -0.1068   0.8496   0.0307
  -6.250  -0.1732   0.01528   0.00955  -0.1066   0.8475   0.0323
  -6.000  -0.1470   0.01493   0.00909  -0.1063   0.8453   0.0343
  -5.750  -0.1213   0.01432   0.00833  -0.1059   0.8430   0.0363
  -5.500  -0.0944   0.01426   0.00831  -0.1058   0.8407   0.0385
  -5.250  -0.0672   0.01420   0.00819  -0.1056   0.8384   0.0410
  -5.000  -0.0396   0.01414   0.00801  -0.1054   0.8364   0.0432
  -4.750  -0.0142   0.01347   0.00729  -0.1051   0.8340   0.0463
  -4.500   0.0124   0.01340   0.00723  -0.1048   0.8306   0.0492
  -4.250   0.0392   0.01324   0.00699  -0.1044   0.8267   0.0518
  -4.000   0.0652   0.01263   0.00629  -0.1040   0.8233   0.0549
  -3.750   0.0921   0.01236   0.00600  -0.1038   0.8204   0.0580
  -3.500   0.1189   0.01218   0.00578  -0.1035   0.8176   0.0608
  -3.250   0.1457   0.01201   0.00559  -0.1032   0.8139   0.0635
  -3.000   0.1727   0.01183   0.00535  -0.1029   0.8098   0.0651
  -2.750   0.1983   0.01116   0.00464  -0.1024   0.8058   0.0689
  -2.500   0.2244   0.01091   0.00438  -0.1019   0.8007   0.0714
  -2.250   0.2507   0.01065   0.00410  -0.1013   0.7944   0.0741
  -2.000   0.2781   0.01046   0.00384  -0.1010   0.7898   0.0766
  -1.750   0.3044   0.01028   0.00365  -0.1005   0.7850   0.0781
  -1.500   0.3304   0.00993   0.00331  -0.1000   0.7803   0.0824
  -1.250   0.3576   0.00973   0.00310  -0.0998   0.7761   0.0867
  -1.000   0.3845   0.00958   0.00294  -0.0994   0.7717   0.0910
  -0.750   0.4109   0.00936   0.00277  -0.0990   0.7662   0.0999
  -0.500   0.4377   0.00910   0.00261  -0.0986   0.7615   0.1310
  -0.250   0.4633   0.00873   0.00255  -0.0982   0.7568   0.2290
   0.000   0.4877   0.00830   0.00251  -0.0976   0.7504   0.3502
   0.250   0.5069   0.00742   0.00246  -0.0960   0.7449   0.6408
   0.500   0.5825   0.00663   0.00247  -0.1058   0.7376   0.9904
   0.750   0.6239   0.00658   0.00235  -0.1086   0.7300   1.0000
   1.000   0.6482   0.00656   0.00231  -0.1078   0.7205   1.0000
   1.250   0.6725   0.00655   0.00225  -0.1069   0.7095   1.0000
   1.500   0.6965   0.00654   0.00219  -0.1059   0.6949   1.0000
   1.750   0.7199   0.00657   0.00213  -0.1048   0.6745   1.0000
   2.000   0.7421   0.00667   0.00209  -0.1035   0.6474   1.0000
   2.250   0.7624   0.00689   0.00211  -0.1018   0.6130   1.0000
   2.500   0.7810   0.00722   0.00222  -0.0999   0.5682   1.0000
   2.750   0.7961   0.00774   0.00242  -0.0973   0.5042   1.0000
   3.000   0.8112   0.00830   0.00268  -0.0948   0.4514   1.0000
   3.250   0.8296   0.00873   0.00292  -0.0930   0.4209   1.0000
   3.500   0.8495   0.00909   0.00315  -0.0915   0.3982   1.0000
   3.750   0.8704   0.00940   0.00336  -0.0902   0.3775   1.0000
   4.000   0.8915   0.00970   0.00357  -0.0890   0.3584   1.0000
   4.250   0.9125   0.01001   0.00379  -0.0877   0.3402   1.0000
   4.500   0.9335   0.01032   0.00402  -0.0864   0.3236   1.0000
   4.750   0.9547   0.01063   0.00425  -0.0852   0.3088   1.0000
   5.000   0.9762   0.01092   0.00448  -0.0841   0.2961   1.0000
   5.250   0.9975   0.01121   0.00472  -0.0829   0.2842   1.0000
   5.500   1.0184   0.01152   0.00499  -0.0817   0.2735   1.0000
   5.750   1.0388   0.01185   0.00526  -0.0804   0.2641   1.0000
   6.000   1.0608   0.01210   0.00550  -0.0794   0.2561   1.0000
   6.250   1.0807   0.01245   0.00581  -0.0781   0.2490   1.0000
   6.500   1.1028   0.01267   0.00606  -0.0771   0.2422   1.0000
   6.750   1.1224   0.01301   0.00636  -0.0757   0.2349   1.0000
   7.000   1.1439   0.01325   0.00663  -0.0747   0.2278   1.0000
   7.500   1.1826   0.01382   0.00721  -0.0718   0.2116   1.0000
   7.750   1.2000   0.01416   0.00752  -0.0700   0.2018   1.0000
   8.000   1.2176   0.01451   0.00783  -0.0684   0.1857   1.0000
   8.250   1.2254   0.01543   0.00839  -0.0653   0.1286   1.0000
   8.500   1.2155   0.01759   0.01001  -0.0598   0.0440   1.0000
   8.750   1.2271   0.01847   0.01089  -0.0575   0.0357   1.0000
   9.000   1.2418   0.01914   0.01163  -0.0557   0.0327   1.0000
   9.250   1.2532   0.02005   0.01257  -0.0535   0.0297   1.0000
   9.500   1.2647   0.02095   0.01355  -0.0515   0.0276   1.0000
   9.750   1.2777   0.02176   0.01443  -0.0497   0.0262   1.0000
  10.000   1.2887   0.02271   0.01544  -0.0478   0.0249   1.0000
  10.250   1.2967   0.02389   0.01669  -0.0456   0.0236   1.0000
  10.500   1.2960   0.02570   0.01861  -0.0427   0.0225   1.0000
  10.750   1.3071   0.02671   0.01969  -0.0411   0.0217   1.0000
  11.000   1.3164   0.02788   0.02094  -0.0395   0.0208   1.0000
  11.250   1.3234   0.02925   0.02240  -0.0377   0.0201   1.0000
  11.500   1.3286   0.03079   0.02401  -0.0359   0.0195   1.0000
  11.750   1.3334   0.03239   0.02567  -0.0343   0.0188   1.0000
  12.000   1.3346   0.03434   0.02769  -0.0325   0.0184   1.0000
  12.250   1.3318   0.03669   0.03013  -0.0306   0.0180   1.0000
  12.500   1.3204   0.03995   0.03348  -0.0284   0.0174   1.0000
  12.750   1.3246   0.04187   0.03550  -0.0273   0.0172   1.0000
  13.000   1.3305   0.04371   0.03745  -0.0264   0.0167   1.0000
  13.250   1.3345   0.04579   0.03962  -0.0256   0.0162   1.0000
  13.500   1.3363   0.04816   0.04209  -0.0249   0.0158   1.0000
  13.750   1.3373   0.05073   0.04474  -0.0242   0.0154   1.0000
  14.000   1.3392   0.05329   0.04738  -0.0239   0.0150   1.0000
  14.250   1.3399   0.05606   0.05023  -0.0236   0.0147   1.0000
  14.500   1.3398   0.05900   0.05323  -0.0234   0.0144   1.0000
  14.750   1.3400   0.06196   0.05626  -0.0233   0.0142   1.0000
  15.000   1.3407   0.06488   0.05925  -0.0232   0.0140   1.0000
  15.250   1.3432   0.06735   0.06175  -0.0215   0.0135   1.0000
  15.500   1.3420   0.07081   0.06537  -0.0223   0.0133   1.0000
  15.750   1.3438   0.07384   0.06852  -0.0224   0.0132   1.0000
  16.000   1.3433   0.07731   0.07213  -0.0230   0.0130   1.0000
  16.250   1.3423   0.08091   0.07587  -0.0236   0.0128   1.0000
  16.500   1.3403   0.08474   0.07985  -0.0245   0.0125   1.0000
  16.750   1.3381   0.08868   0.08392  -0.0256   0.0123   1.0000
  17.000   1.3351   0.09283   0.08820  -0.0270   0.0121   1.0000
  17.250   1.3316   0.09715   0.09263  -0.0287   0.0118   1.0000
  17.500   1.3269   0.10168   0.09731  -0.0302   0.0117   1.0000
  17.750   1.3229   0.10620   0.10194  -0.0322   0.0115   1.0000
  18.000   1.3172   0.11110   0.10699  -0.0342   0.0114   1.0000
  18.250   1.3134   0.11571   0.11169  -0.0365   0.0113   1.0000
  18.500   1.3071   0.12084   0.11694  -0.0391   0.0111   1.0000
  18.750   1.2998   0.12624   0.12247  -0.0419   0.0111   1.0000
  19.000   1.2916   0.13192   0.12829  -0.0450   0.0110   1.0000
  19.250   1.2793   0.13863   0.13518  -0.0488   0.0110   1.0000
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