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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 50,000
Max Cl/Cd: 37.23 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe488-il-50000.txt
Download as CSV file: xf-goe488-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4373   0.10488   0.09806  -0.0207   1.0000   0.1863
  -7.750  -0.4093   0.09835   0.09143  -0.0185   1.0000   0.1981
  -7.500  -0.4329   0.09844   0.09173  -0.0195   1.0000   0.2008
  -7.250  -0.4151   0.09340   0.08667  -0.0165   1.0000   0.2125
  -7.000  -0.4380   0.09355   0.08699  -0.0197   1.0000   0.2159
  -6.750  -0.4210   0.08848   0.08193  -0.0157   1.0000   0.2281
  -6.250  -0.4328   0.08454   0.07815  -0.0167   1.0000   0.2450
  -6.000  -0.4206   0.08013   0.07379  -0.0127   1.0000   0.2550
  -5.250  -0.4211   0.07212   0.06593  -0.0097   1.0000   0.2922
  -5.000  -0.4181   0.06938   0.06324  -0.0073   1.0000   0.3099
  -4.750  -0.4190   0.06693   0.06081  -0.0060   1.0000   0.3341
  -4.500  -0.4179   0.06441   0.05834  -0.0032   1.0000   0.3627
  -4.250  -0.4158   0.06161   0.05562   0.0016   1.0000   0.3939
  -3.500  -0.4195   0.05469   0.04896   0.0194   1.0000   0.5249
  -3.250  -0.4160   0.05200   0.04637   0.0269   1.0000   0.5653
  -3.000  -0.4162   0.04960   0.04400   0.0319   1.0000   0.6014
  -2.750  -0.4101   0.04705   0.04150   0.0352   1.0000   0.6258
  -2.500  -0.4015   0.04433   0.03879   0.0359   1.0000   0.6400
  -2.250  -0.1893   0.03640   0.02757  -0.0298   1.0000   0.1977
  -2.000  -0.1602   0.03389   0.02457  -0.0303   1.0000   0.1800
  -1.750  -0.1310   0.03188   0.02195  -0.0304   1.0000   0.1695
  -1.500  -0.1055   0.03018   0.01996  -0.0301   1.0000   0.1663
  -1.250  -0.0801   0.02886   0.01828  -0.0297   1.0000   0.1674
  -1.000  -0.0545   0.02784   0.01684  -0.0291   1.0000   0.1714
  -0.750  -0.0299   0.02669   0.01563  -0.0287   1.0000   0.1751
  -0.500  -0.0061   0.02582   0.01460  -0.0279   1.0000   0.1792
  -0.250   0.0192   0.02513   0.01359  -0.0271   1.0000   0.1863
   0.000   0.0461   0.02450   0.01291  -0.0268   1.0000   0.1993
   0.250   0.0709   0.02400   0.01249  -0.0264   1.0000   0.2263
   0.500   0.0964   0.02318   0.01189  -0.0259   1.0000   0.2780
   0.750   0.1333   0.02024   0.01061  -0.0268   1.0000   1.0000
   1.000   0.1527   0.02067   0.01075  -0.0259   1.0000   1.0000
   1.250   0.1714   0.02116   0.01104  -0.0251   1.0000   1.0000
   1.500   0.1897   0.02170   0.01143  -0.0244   1.0000   1.0000
   1.750   0.2074   0.02230   0.01193  -0.0237   1.0000   1.0000
   2.000   0.2244   0.02298   0.01254  -0.0231   1.0000   1.0000
   2.250   0.2439   0.02381   0.01332  -0.0234   0.9983   1.0000
   2.500   0.3186   0.02546   0.01494  -0.0338   0.9708   1.0000
   2.750   0.3881   0.02649   0.01603  -0.0424   0.9403   1.0000
   3.000   0.4522   0.02699   0.01665  -0.0493   0.9061   1.0000
   3.250   0.5242   0.02691   0.01678  -0.0564   0.8710   1.0000
   3.500   0.5903   0.02624   0.01634  -0.0615   0.8319   1.0000
   3.750   0.6616   0.02487   0.01524  -0.0662   0.7951   1.0000
   4.000   0.7124   0.02366   0.01417  -0.0671   0.7540   1.0000
   4.250   0.7526   0.02278   0.01335  -0.0664   0.7120   1.0000
   4.500   0.7873   0.02233   0.01286  -0.0652   0.6714   1.0000
   4.750   0.8195   0.02232   0.01275  -0.0641   0.6341   1.0000
   5.000   0.8469   0.02280   0.01318  -0.0629   0.5993   1.0000
   5.250   0.8730   0.02345   0.01377  -0.0617   0.5676   1.0000
   5.500   0.8975   0.02423   0.01453  -0.0604   0.5380   1.0000
   5.750   0.9211   0.02511   0.01542  -0.0590   0.5099   1.0000
   6.000   0.9445   0.02612   0.01650  -0.0577   0.4830   1.0000
   6.250   0.9669   0.02716   0.01754  -0.0561   0.4549   1.0000
   6.500   0.9882   0.02825   0.01862  -0.0544   0.4258   1.0000
   6.750   1.0081   0.02933   0.01968  -0.0524   0.3955   1.0000
   7.000   1.0271   0.03044   0.02080  -0.0504   0.3656   1.0000
   7.250   1.0450   0.03153   0.02197  -0.0483   0.3348   1.0000
   7.500   1.0598   0.03209   0.02240  -0.0456   0.2979   1.0000
   7.750   1.0667   0.03200   0.02221  -0.0416   0.2550   1.0000
   8.000   1.0673   0.03227   0.02244  -0.0369   0.2062   1.0000
   8.250   1.0696   0.03394   0.02357  -0.0327   0.1555   1.0000
   8.500   1.0840   0.03688   0.02637  -0.0304   0.1244   1.0000
   8.750   1.1043   0.03991   0.02954  -0.0289   0.1097   1.0000
   9.000   1.1225   0.04280   0.03254  -0.0275   0.1004   1.0000
   9.250   1.1380   0.04553   0.03552  -0.0258   0.0932   1.0000
   9.500   1.1538   0.04925   0.03944  -0.0244   0.0897   1.0000
   9.750   1.1588   0.05319   0.04398  -0.0219   0.0884   1.0000
  10.000   1.1586   0.05736   0.04865  -0.0193   0.0877   1.0000
  10.250   1.1534   0.06165   0.05338  -0.0166   0.0876   1.0000
  10.500   1.1431   0.06603   0.05812  -0.0141   0.0879   1.0000
  10.750   1.1278   0.07041   0.06281  -0.0117   0.0882   1.0000
  11.000   1.1093   0.07461   0.06721  -0.0094   0.0888   1.0000
  11.250   1.0897   0.07915   0.07190  -0.0080   0.0894   1.0000
  11.500   1.0714   0.08418   0.07706  -0.0079   0.0900   1.0000
  11.750   0.9715   0.09891   0.09206  -0.0195   0.0970   1.0000
  12.000   0.9449   0.10997   0.10304  -0.0265   0.1006   1.0000
  12.250   0.9356   0.11779   0.11082  -0.0300   0.1023   1.0000
  12.500   0.9353   0.12384   0.11686  -0.0315   0.1033   1.0000
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