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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 500,000
Max Cl/Cd: 96.7 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe509-il-500000.txt
Download as CSV file: xf-goe509-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2640   0.08839   0.08624  -0.0489   0.9897   0.0261
  -8.500  -0.2602   0.08016   0.07802  -0.0625   0.9849   0.0274
  -8.250  -0.2613   0.07335   0.07121  -0.0693   0.9779   0.0278
  -8.000  -0.2426   0.06867   0.06650  -0.0746   0.9740   0.0279
  -7.750  -0.2179   0.06567   0.06347  -0.0785   0.9721   0.0284
  -7.500  -0.2627   0.03382   0.03073  -0.0948   0.9583   0.0227
  -7.250  -0.2778   0.02529   0.02127  -0.0911   0.9465   0.0229
  -7.000  -0.2585   0.02298   0.01873  -0.0904   0.9406   0.0235
  -6.750  -0.2311   0.02309   0.01892  -0.0903   0.9336   0.0242
  -6.500  -0.2053   0.02110   0.01662  -0.0904   0.9290   0.0251
  -6.250  -0.1943   0.01931   0.01449  -0.0870   0.9152   0.0261
  -6.000  -0.1769   0.01821   0.01304  -0.0845   0.9001   0.0274
  -5.750  -0.1555   0.01657   0.01121  -0.0834   0.8856   0.0286
  -5.500  -0.1243   0.01604   0.01061  -0.0840   0.8717   0.0299
  -5.250  -0.0926   0.01518   0.00952  -0.0846   0.8569   0.0314
  -5.000  -0.0622   0.01470   0.00875  -0.0848   0.8417   0.0330
  -4.750  -0.0359   0.01362   0.00752  -0.0846   0.8278   0.0349
  -4.500  -0.0095   0.01336   0.00716  -0.0842   0.8154   0.0366
  -4.250   0.0166   0.01298   0.00663  -0.0836   0.8046   0.0383
  -4.000   0.0427   0.01278   0.00627  -0.0830   0.7940   0.0398
  -3.750   0.0667   0.01201   0.00545  -0.0821   0.7837   0.0422
  -3.500   0.0921   0.01180   0.00518  -0.0815   0.7742   0.0443
  -3.250   0.1170   0.01155   0.00487  -0.0807   0.7645   0.0463
  -3.000   0.1425   0.01141   0.00464  -0.0799   0.7558   0.0481
  -2.750   0.1661   0.01082   0.00401  -0.0789   0.7468   0.0508
  -2.500   0.1905   0.01060   0.00377  -0.0781   0.7377   0.0534
  -2.000   0.2397   0.01032   0.00339  -0.0763   0.7181   0.0586
  -1.750   0.2622   0.00996   0.00302  -0.0750   0.7073   0.0637
  -1.500   0.2860   0.00986   0.00286  -0.0740   0.6955   0.0686
  -1.250   0.3085   0.00967   0.00265  -0.0726   0.6813   0.0766
  -1.000   0.3308   0.00956   0.00249  -0.0713   0.6648   0.0874
  -0.750   0.3515   0.00938   0.00234  -0.0696   0.6450   0.1139
  -0.500   0.3684   0.00906   0.00236  -0.0674   0.6214   0.2419
  -0.250   0.3886   0.00913   0.00238  -0.0656   0.5918   0.2780
   0.000   0.4077   0.00928   0.00239  -0.0636   0.5555   0.2966
   0.250   0.4262   0.00948   0.00242  -0.0616   0.5177   0.3118
   1.000   0.4883   0.00990   0.00259  -0.0570   0.4639   0.3581
   1.250   0.5100   0.00997   0.00265  -0.0558   0.4547   0.3755
   1.750   0.5411   0.00945   0.00270  -0.0507   0.4420   0.6028
   2.250   0.7589   0.00996   0.00391  -0.0863   0.4212   0.9890
   2.500   0.8026   0.01017   0.00405  -0.0898   0.4148   0.9941
   2.750   0.8476   0.01030   0.00410  -0.0938   0.4093   0.9978
   3.000   0.8855   0.01033   0.00414  -0.0961   0.4043   1.0000
   3.250   0.9064   0.01045   0.00422  -0.0948   0.3997   1.0000
   3.500   0.9265   0.01064   0.00435  -0.0933   0.3943   1.0000
   3.750   0.9483   0.01070   0.00444  -0.0921   0.3902   1.0000
   4.000   0.9695   0.01079   0.00453  -0.0907   0.3843   1.0000
   4.250   0.9899   0.01094   0.00465  -0.0893   0.3796   1.0000
   4.500   1.0111   0.01104   0.00476  -0.0880   0.3740   1.0000
   4.750   1.0324   0.01113   0.00488  -0.0867   0.3688   1.0000
   5.000   1.0525   0.01129   0.00500  -0.0852   0.3631   1.0000
   5.250   1.0737   0.01138   0.00512  -0.0839   0.3569   1.0000
   5.500   1.0938   0.01151   0.00525  -0.0824   0.3490   1.0000
   5.750   1.1141   0.01164   0.00538  -0.0810   0.3412   1.0000
   6.000   1.1336   0.01179   0.00552  -0.0794   0.3324   1.0000
   6.250   1.1536   0.01193   0.00567  -0.0779   0.3228   1.0000
   6.500   1.1718   0.01212   0.00584  -0.0760   0.3090   1.0000
   6.750   1.1885   0.01238   0.00603  -0.0739   0.2907   1.0000
   7.000   1.2025   0.01276   0.00629  -0.0714   0.2681   1.0000
   7.250   1.2147   0.01321   0.00662  -0.0685   0.2445   1.0000
   7.500   1.2260   0.01368   0.00699  -0.0655   0.2258   1.0000
   8.000   1.2470   0.01446   0.00768  -0.0590   0.2027   1.0000
   8.250   1.2581   0.01485   0.00804  -0.0560   0.1941   1.0000
   8.500   1.2691   0.01527   0.00844  -0.0530   0.1858   1.0000
   8.750   1.2820   0.01565   0.00883  -0.0504   0.1784   1.0000
   9.000   1.2934   0.01612   0.00927  -0.0476   0.1709   1.0000
   9.250   1.3073   0.01650   0.00967  -0.0453   0.1635   1.0000
   9.500   1.3180   0.01705   0.01020  -0.0426   0.1548   1.0000
   9.750   1.3310   0.01753   0.01065  -0.0403   0.1428   1.0000
  10.000   1.3419   0.01813   0.01119  -0.0377   0.1252   1.0000
  10.250   1.3354   0.01966   0.01239  -0.0328   0.0797   1.0000
  10.500   1.3293   0.02126   0.01382  -0.0282   0.0466   1.0000
  10.750   1.3312   0.02249   0.01501  -0.0249   0.0392   1.0000
  11.000   1.3369   0.02357   0.01614  -0.0223   0.0360   1.0000
  11.250   1.3443   0.02459   0.01725  -0.0200   0.0344   1.0000
  11.500   1.3499   0.02578   0.01854  -0.0177   0.0330   1.0000
  11.750   1.3531   0.02721   0.02007  -0.0153   0.0317   1.0000
  12.000   1.3541   0.02890   0.02185  -0.0131   0.0306   1.0000
  12.250   1.3511   0.03102   0.02407  -0.0108   0.0293   1.0000
  12.500   1.3478   0.03328   0.02645  -0.0089   0.0285   1.0000
  12.750   1.3521   0.03501   0.02828  -0.0076   0.0277   1.0000
  13.000   1.3529   0.03711   0.03049  -0.0064   0.0269   1.0000
  13.250   1.3518   0.03951   0.03298  -0.0053   0.0261   1.0000
  13.500   1.3490   0.04218   0.03575  -0.0044   0.0253   1.0000
  13.750   1.3425   0.04537   0.03904  -0.0036   0.0248   1.0000
  14.000   1.3360   0.04871   0.04248  -0.0032   0.0242   1.0000
  14.250   1.3245   0.05278   0.04665  -0.0031   0.0236   1.0000
  14.500   1.3043   0.05808   0.05206  -0.0032   0.0230   1.0000
  14.750   1.3001   0.06163   0.05572  -0.0035   0.0226   1.0000
  15.000   1.2996   0.06483   0.05903  -0.0039   0.0221   1.0000
  15.250   1.2939   0.06870   0.06300  -0.0045   0.0219   1.0000
  15.500   1.2911   0.07233   0.06673  -0.0051   0.0213   1.0000
  15.750   1.2852   0.07635   0.07084  -0.0058   0.0207   1.0000
  16.000   1.2819   0.08009   0.07466  -0.0066   0.0202   1.0000
  16.250   1.2770   0.08399   0.07863  -0.0074   0.0199   1.0000
  16.500   1.2729   0.08783   0.08254  -0.0083   0.0194   1.0000
  16.750   1.2677   0.09176   0.08653  -0.0091   0.0191   1.0000
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