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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 500,000
Max Cl/Cd: 91.11 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe509-il-500000-n5.txt
Download as CSV file: xf-goe509-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2647   0.10834   0.10593  -0.0525   0.9881   0.0089
 -11.000  -0.2569   0.10388   0.10149  -0.0559   0.9865   0.0093
 -10.000  -0.5059   0.02820   0.02480  -0.1011   0.9575   0.0106
  -9.750  -0.4964   0.02447   0.02061  -0.1004   0.9524   0.0109
  -9.500  -0.4747   0.02221   0.01799  -0.1007   0.9494   0.0113
  -9.250  -0.4655   0.02090   0.01645  -0.0975   0.9415   0.0116
  -9.000  -0.4441   0.01945   0.01475  -0.0969   0.9366   0.0119
  -8.750  -0.4287   0.01859   0.01377  -0.0946   0.9288   0.0123
  -8.500  -0.4066   0.01782   0.01288  -0.0937   0.9214   0.0128
  -8.250  -0.3916   0.01726   0.01222  -0.0910   0.9085   0.0132
  -7.750  -0.3396   0.01569   0.01031  -0.0904   0.8749   0.0145
  -7.500  -0.3049   0.01490   0.00930  -0.0919   0.8548   0.0154
  -7.250  -0.2737   0.01450   0.00873  -0.0925   0.8339   0.0163
  -7.000  -0.2476   0.01415   0.00820  -0.0921   0.8173   0.0171
  -6.750  -0.2231   0.01377   0.00764  -0.0913   0.8047   0.0181
  -6.500  -0.1991   0.01339   0.00711  -0.0904   0.7937   0.0191
  -6.250  -0.1743   0.01320   0.00684  -0.0897   0.7835   0.0202
  -6.000  -0.1492   0.01304   0.00660  -0.0890   0.7737   0.0215
  -5.750  -0.1247   0.01278   0.00621  -0.0882   0.7641   0.0228
  -5.500  -0.1005   0.01249   0.00582  -0.0874   0.7550   0.0241
  -5.250  -0.0753   0.01230   0.00559  -0.0867   0.7473   0.0253
  -5.000  -0.0502   0.01217   0.00538  -0.0860   0.7390   0.0269
  -4.750  -0.0252   0.01196   0.00509  -0.0853   0.7304   0.0282
  -4.500  -0.0010   0.01170   0.00474  -0.0844   0.7213   0.0297
  -4.250   0.0241   0.01151   0.00453  -0.0837   0.7128   0.0312
  -4.000   0.0488   0.01140   0.00434  -0.0829   0.7034   0.0328
  -3.750   0.0734   0.01124   0.00411  -0.0821   0.6918   0.0343
  -3.500   0.0980   0.01113   0.00391  -0.0813   0.6803   0.0354
  -3.250   0.1215   0.01087   0.00360  -0.0803   0.6692   0.0374
  -3.000   0.1458   0.01074   0.00342  -0.0794   0.6577   0.0391
  -2.750   0.1702   0.01063   0.00325  -0.0785   0.6459   0.0408
  -2.500   0.1943   0.01054   0.00308  -0.0776   0.6328   0.0426
  -2.250   0.2180   0.01046   0.00293  -0.0766   0.6181   0.0438
  -2.000   0.2408   0.01034   0.00273  -0.0754   0.6001   0.0467
  -1.750   0.2628   0.01033   0.00263  -0.0741   0.5764   0.0497
  -1.500   0.2833   0.01040   0.00253  -0.0724   0.5401   0.0526
  -1.250   0.3025   0.01053   0.00247  -0.0705   0.4984   0.0557
  -0.500   0.3665   0.01075   0.00241  -0.0663   0.4387   0.0785
  -0.250   0.3892   0.01075   0.00240  -0.0652   0.4311   0.0952
   0.000   0.4115   0.01065   0.00239  -0.0641   0.4246   0.1303
   0.250   0.4322   0.01050   0.00245  -0.0626   0.4193   0.2139
   0.500   0.4554   0.01051   0.00252  -0.0616   0.4151   0.2507
   0.750   0.4795   0.01054   0.00257  -0.0608   0.4112   0.2723
   1.000   0.5031   0.01058   0.00263  -0.0599   0.4068   0.2903
   1.250   0.5260   0.01066   0.00268  -0.0589   0.4015   0.3037
   1.500   0.5496   0.01069   0.00273  -0.0579   0.3969   0.3166
   1.750   0.5732   0.01071   0.00279  -0.0570   0.3926   0.3316
   2.000   0.5961   0.01074   0.00285  -0.0560   0.3889   0.3515
   2.250   0.6184   0.01078   0.00292  -0.0549   0.3852   0.3700
   2.500   0.6410   0.01079   0.00298  -0.0538   0.3820   0.3917
   2.750   0.6612   0.01062   0.00303  -0.0523   0.3781   0.4690
   3.750   0.8965   0.01071   0.00416  -0.0805   0.3451   0.9888
   4.000   0.9309   0.01090   0.00431  -0.0821   0.3372   0.9925
   4.250   0.9663   0.01106   0.00444  -0.0840   0.3280   0.9954
   4.500   1.0044   0.01124   0.00457  -0.0865   0.3175   0.9983
   4.750   1.0379   0.01140   0.00470  -0.0880   0.3068   1.0000
   5.000   1.0569   0.01160   0.00484  -0.0864   0.2941   1.0000
   5.250   1.0750   0.01185   0.00502  -0.0845   0.2790   1.0000
   5.500   1.0908   0.01219   0.00525  -0.0823   0.2585   1.0000
   5.750   1.1049   0.01262   0.00555  -0.0798   0.2339   1.0000
   6.000   1.1188   0.01306   0.00587  -0.0772   0.2136   1.0000
   6.250   1.1340   0.01342   0.00617  -0.0749   0.2014   1.0000
   6.500   1.1495   0.01375   0.00646  -0.0726   0.1920   1.0000
   6.750   1.1635   0.01408   0.00676  -0.0700   0.1836   1.0000
   7.000   1.1763   0.01438   0.00704  -0.0672   0.1775   1.0000
   7.250   1.1892   0.01467   0.00732  -0.0644   0.1725   1.0000
   7.500   1.2039   0.01491   0.00760  -0.0620   0.1694   1.0000
   7.750   1.2180   0.01521   0.00791  -0.0595   0.1653   1.0000
   8.000   1.2314   0.01556   0.00825  -0.0570   0.1604   1.0000
   8.250   1.2461   0.01588   0.00859  -0.0547   0.1566   1.0000
   8.500   1.2614   0.01619   0.00894  -0.0526   0.1524   1.0000
   8.750   1.2759   0.01656   0.00932  -0.0504   0.1478   1.0000
   9.000   1.2895   0.01699   0.00975  -0.0481   0.1431   1.0000
   9.250   1.3051   0.01734   0.01014  -0.0462   0.1378   1.0000
   9.500   1.3173   0.01788   0.01064  -0.0439   0.1251   1.0000
   9.750   1.3176   0.01905   0.01157  -0.0399   0.0888   1.0000
  10.000   1.3218   0.02005   0.01251  -0.0366   0.0746   1.0000
  10.250   1.3295   0.02091   0.01337  -0.0339   0.0609   1.0000
  10.500   1.3263   0.02245   0.01477  -0.0300   0.0373   1.0000
  10.750   1.3335   0.02343   0.01579  -0.0276   0.0342   1.0000
  11.000   1.3416   0.02442   0.01683  -0.0254   0.0320   1.0000
  11.250   1.3512   0.02535   0.01784  -0.0235   0.0309   1.0000
  11.500   1.3602   0.02636   0.01893  -0.0217   0.0296   1.0000
  11.750   1.3683   0.02750   0.02015  -0.0200   0.0285   1.0000
  12.000   1.3740   0.02886   0.02158  -0.0182   0.0272   1.0000
  12.250   1.3787   0.03037   0.02316  -0.0165   0.0262   1.0000
  12.500   1.3826   0.03200   0.02488  -0.0149   0.0251   1.0000
  12.750   1.3909   0.03333   0.02630  -0.0137   0.0243   1.0000
  13.000   1.3973   0.03485   0.02791  -0.0126   0.0233   1.0000
  13.250   1.4020   0.03659   0.02974  -0.0115   0.0224   1.0000
  13.500   1.4054   0.03850   0.03173  -0.0105   0.0215   1.0000
  13.750   1.4057   0.04080   0.03409  -0.0095   0.0204   1.0000
  14.000   1.4071   0.04306   0.03644  -0.0087   0.0197   1.0000
  14.250   1.4112   0.04511   0.03859  -0.0082   0.0186   1.0000
  14.500   1.4129   0.04750   0.04107  -0.0077   0.0176   1.0000
  14.750   1.4126   0.05018   0.04383  -0.0074   0.0168   1.0000
  15.000   1.4099   0.05321   0.04693  -0.0072   0.0160   1.0000
  15.250   1.4075   0.05634   0.05016  -0.0073   0.0153   1.0000
  15.500   1.4047   0.05962   0.05355  -0.0074   0.0146   1.0000
  15.750   1.3997   0.06329   0.05731  -0.0078   0.0140   1.0000
  16.000   1.3933   0.06725   0.06138  -0.0084   0.0136   1.0000
  16.250   1.3879   0.07116   0.06535  -0.0091   0.0126   1.0000
  16.500   1.3799   0.07553   0.06981  -0.0101   0.0122   1.0000
  16.750   1.3691   0.08035   0.07475  -0.0111   0.0123   1.0000
  17.000   1.3626   0.08455   0.07907  -0.0121   0.0115   1.0000
  17.250   1.3521   0.08938   0.08400  -0.0133   0.0114   1.0000
  17.500   1.3422   0.09417   0.08891  -0.0146   0.0110   1.0000
  17.750   1.3319   0.09904   0.09387  -0.0159   0.0107   1.0000
  18.000   1.3212   0.10405   0.09898  -0.0174   0.0105   1.0000
  18.250   1.3123   0.10883   0.10385  -0.0189   0.0102   1.0000
  18.500   1.3019   0.11395   0.10905  -0.0205   0.0098   1.0000
  18.750   1.2901   0.11934   0.11453  -0.0224   0.0095   1.0000
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