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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 50,000
Max Cl/Cd: 37.72 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe488-il-50000-n5.txt
Download as CSV file: xf-goe488-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4116   0.10899   0.10174  -0.0221   1.0000   0.1094
  -8.750  -0.4200   0.10757   0.10044  -0.0241   1.0000   0.1135
  -8.500  -0.4346   0.10664   0.09966  -0.0261   1.0000   0.1145
  -8.250  -0.4095   0.10051   0.09346  -0.0231   1.0000   0.1216
  -8.000  -0.4146   0.09845   0.09149  -0.0234   1.0000   0.1263
  -7.750  -0.4319   0.09747   0.09069  -0.0254   1.0000   0.1288
  -7.250  -0.4238   0.09018   0.08350  -0.0239   1.0000   0.1329
  -7.000  -0.4207   0.08720   0.08057  -0.0233   1.0000   0.1360
  -6.750  -0.4215   0.08452   0.07794  -0.0239   1.0000   0.1398
  -6.500  -0.4314   0.08327   0.07666  -0.0299   1.0000   0.1444
  -6.250  -0.4216   0.07869   0.07219  -0.0253   1.0000   0.1474
  -6.000  -0.4184   0.07633   0.06983  -0.0252   1.0000   0.1570
  -5.500  -0.3941   0.06302   0.05586  -0.0360   1.0000   0.0858
  -5.250  -0.3849   0.06002   0.05287  -0.0341   1.0000   0.0836
  -5.000  -0.3737   0.05672   0.04946  -0.0338   1.0000   0.0816
  -4.750  -0.3601   0.05326   0.04582  -0.0340   1.0000   0.0798
  -4.500  -0.3444   0.04975   0.04203  -0.0344   1.0000   0.0782
  -4.250  -0.3273   0.04670   0.03870  -0.0346   1.0000   0.0792
  -4.000  -0.3085   0.04382   0.03548  -0.0348   1.0000   0.0818
  -3.750  -0.2888   0.04100   0.03230  -0.0348   1.0000   0.0819
  -3.500  -0.2682   0.03835   0.02930  -0.0346   1.0000   0.0810
  -3.250  -0.2465   0.03588   0.02643  -0.0343   1.0000   0.0802
  -3.000  -0.2240   0.03370   0.02385  -0.0339   1.0000   0.0798
  -2.750  -0.2010   0.03175   0.02148  -0.0334   1.0000   0.0796
  -2.500  -0.1774   0.03006   0.01939  -0.0329   1.0000   0.0799
  -2.250  -0.1535   0.02860   0.01757  -0.0323   1.0000   0.0805
  -2.000  -0.1293   0.02735   0.01598  -0.0317   1.0000   0.0815
  -1.750  -0.1050   0.02631   0.01461  -0.0310   1.0000   0.0829
  -1.500  -0.0806   0.02549   0.01350  -0.0304   1.0000   0.0859
  -1.250  -0.0589   0.02493   0.01298  -0.0297   1.0000   0.0917
  -1.000  -0.0352   0.02444   0.01230  -0.0290   1.0000   0.0973
  -0.750  -0.0100   0.02393   0.01158  -0.0284   1.0000   0.1009
  -0.500   0.0205   0.02351   0.01114  -0.0293   0.9968   0.1060
  -0.250   0.0628   0.02318   0.01072  -0.0322   0.9880   0.1163
   0.000   0.1079   0.02283   0.01046  -0.0358   0.9774   0.1394
   0.250   0.1531   0.02208   0.01034  -0.0396   0.9640   0.2601
   0.500   0.2124   0.01999   0.01000  -0.0454   0.9512   1.0000
   0.750   0.2582   0.02013   0.00985  -0.0487   0.9359   1.0000
   1.000   0.2986   0.02025   0.00979  -0.0510   0.9224   1.0000
   1.250   0.3355   0.02036   0.00978  -0.0527   0.9093   1.0000
   1.500   0.3720   0.02042   0.00977  -0.0542   0.8956   1.0000
   1.750   0.4094   0.02042   0.00974  -0.0557   0.8812   1.0000
   2.000   0.4467   0.02037   0.00969  -0.0570   0.8664   1.0000
   2.250   0.4836   0.02026   0.00960  -0.0581   0.8503   1.0000
   2.500   0.5159   0.02015   0.00954  -0.0583   0.8313   1.0000
   2.750   0.5464   0.02002   0.00948  -0.0580   0.8098   1.0000
   3.000   0.5765   0.01987   0.00941  -0.0576   0.7853   1.0000
   3.250   0.6048   0.01973   0.00935  -0.0568   0.7563   1.0000
   3.500   0.6332   0.01959   0.00927  -0.0559   0.7210   1.0000
   3.750   0.6644   0.01941   0.00912  -0.0553   0.6800   1.0000
   4.000   0.6981   0.01931   0.00888  -0.0549   0.6333   1.0000
   4.250   0.7276   0.01952   0.00886  -0.0541   0.5842   1.0000
   4.500   0.7519   0.01998   0.00915  -0.0529   0.5387   1.0000
   4.750   0.7747   0.02054   0.00955  -0.0516   0.5004   1.0000
   5.000   0.7974   0.02114   0.01003  -0.0504   0.4697   1.0000
   5.250   0.8203   0.02179   0.01061  -0.0493   0.4439   1.0000
   5.500   0.8438   0.02247   0.01127  -0.0484   0.4220   1.0000
   5.750   0.8675   0.02317   0.01202  -0.0476   0.4014   1.0000
   6.000   0.8917   0.02390   0.01283  -0.0469   0.3822   1.0000
   6.250   0.9158   0.02467   0.01365  -0.0461   0.3632   1.0000
   6.500   0.9383   0.02544   0.01455  -0.0452   0.3430   1.0000
   6.750   0.9597   0.02621   0.01551  -0.0440   0.3221   1.0000
   7.000   0.9769   0.02688   0.01628  -0.0422   0.2970   1.0000
   7.250   0.9891   0.02738   0.01688  -0.0398   0.2652   1.0000
   7.500   1.0017   0.02790   0.01750  -0.0374   0.2317   1.0000
   7.750   1.0153   0.02858   0.01821  -0.0353   0.1973   1.0000
   8.000   1.0270   0.02963   0.01913  -0.0333   0.1541   1.0000
   8.250   1.0374   0.03142   0.02067  -0.0313   0.0996   1.0000
   8.500   1.0468   0.03366   0.02264  -0.0293   0.0675   1.0000
   8.750   1.0539   0.03595   0.02488  -0.0269   0.0575   1.0000
   9.000   1.0609   0.03812   0.02718  -0.0245   0.0514   1.0000
   9.250   1.0647   0.04047   0.02955  -0.0219   0.0477   1.0000
   9.500   1.0734   0.04240   0.03181  -0.0196   0.0436   1.0000
   9.750   1.0789   0.04449   0.03407  -0.0173   0.0403   1.0000
  10.000   1.0828   0.04673   0.03642  -0.0152   0.0383   1.0000
  10.250   1.0887   0.04924   0.03908  -0.0132   0.0370   1.0000
  10.500   1.0961   0.05189   0.04205  -0.0114   0.0359   1.0000
  10.750   1.1009   0.05477   0.04525  -0.0097   0.0350   1.0000
  11.000   1.1019   0.05792   0.04879  -0.0081   0.0342   1.0000
  11.250   1.0991   0.06125   0.05242  -0.0069   0.0336   1.0000
  11.500   1.0927   0.06491   0.05635  -0.0061   0.0330   1.0000
  11.750   1.0833   0.06895   0.06065  -0.0059   0.0326   1.0000
  12.000   1.0712   0.07347   0.06542  -0.0065   0.0323   1.0000
  12.250   1.0560   0.07885   0.07103  -0.0082   0.0322   1.0000
  12.500   1.0378   0.08516   0.07758  -0.0112   0.0324   1.0000
  12.750   1.0155   0.09313   0.08578  -0.0158   0.0332   1.0000
  13.000   0.9930   0.10214   0.09499  -0.0215   0.0339   1.0000
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