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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.74 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802b-il-1000000.txt
Download as CSV file: xf-goe802b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2665   0.08532   0.08365  -0.0421   0.9347   0.0172
  -8.000  -0.2592   0.08256   0.08087  -0.0423   0.9240   0.0174
  -7.750  -0.2492   0.07986   0.07812  -0.0439   0.9135   0.0175
  -7.500  -0.2367   0.07710   0.07534  -0.0464   0.9035   0.0177
  -7.250  -0.2228   0.07429   0.07248  -0.0492   0.8941   0.0179
  -7.000  -0.2068   0.07125   0.06940  -0.0527   0.8850   0.0183
  -6.750  -0.1894   0.06800   0.06609  -0.0565   0.8765   0.0189
  -6.500  -0.1694   0.06447   0.06252  -0.0608   0.8676   0.0197
  -6.250  -0.1384   0.05969   0.05758  -0.0689   0.8588   0.0206
  -6.000  -0.1122   0.05553   0.05331  -0.0739   0.8498   0.0207
  -5.750  -0.0876   0.05182   0.04946  -0.0772   0.8412   0.0208
  -5.500  -0.0626   0.04809   0.04561  -0.0801   0.8327   0.0208
  -5.250  -0.0461   0.04395   0.04138  -0.0817   0.8244   0.0212
  -5.000  -0.0238   0.04180   0.03918  -0.0829   0.8159   0.0214
  -4.750  -0.0001   0.03972   0.03699  -0.0840   0.8067   0.0217
  -4.500   0.0251   0.03760   0.03477  -0.0853   0.7978   0.0221
  -4.250   0.0511   0.03543   0.03246  -0.0864   0.7888   0.0228
  -4.000   0.0789   0.03309   0.02998  -0.0875   0.7803   0.0239
  -3.750   0.1122   0.03093   0.02747  -0.0881   0.7711   0.0249
  -3.500   0.1394   0.02893   0.02529  -0.0885   0.7615   0.0250
  -3.250   0.1628   0.02552   0.02169  -0.0894   0.7513   0.0255
  -3.000   0.1888   0.02423   0.02032  -0.0898   0.7396   0.0259
  -2.750   0.2152   0.02310   0.01907  -0.0901   0.7269   0.0264
  -2.500   0.2422   0.02200   0.01781  -0.0903   0.7126   0.0273
  -2.250   0.2725   0.02163   0.01715  -0.0898   0.6969   0.0297
  -2.000   0.2996   0.01921   0.01443  -0.0900   0.6817   0.0302
  -1.750   0.3263   0.01819   0.01329  -0.0902   0.6647   0.0306
  -1.500   0.3533   0.01747   0.01244  -0.0904   0.6465   0.0310
  -1.250   0.3806   0.01685   0.01169  -0.0905   0.6284   0.0318
  -1.000   0.4085   0.01627   0.01095  -0.0905   0.6111   0.0336
  -0.750   0.4375   0.01618   0.01065  -0.0901   0.5954   0.0352
   0.250   0.5466   0.00987   0.00343  -0.0901   0.5444   0.0305
   0.500   0.5739   0.00958   0.00309  -0.0901   0.5330   0.0305
   0.750   0.6012   0.00937   0.00284  -0.0901   0.5210   0.0305
   1.000   0.6289   0.00920   0.00265  -0.0901   0.5099   0.0309
   1.250   0.6566   0.00913   0.00255  -0.0901   0.4979   0.0316
   1.500   0.6843   0.00914   0.00250  -0.0901   0.4838   0.0326
   1.750   0.7121   0.00916   0.00248  -0.0901   0.4691   0.0337
   2.000   0.7399   0.00922   0.00249  -0.0901   0.4556   0.0348
   2.250   0.7678   0.00932   0.00255  -0.0901   0.4436   0.0359
   2.500   0.7954   0.00945   0.00264  -0.0901   0.4303   0.0386
   2.750   0.8233   0.00964   0.00286  -0.0900   0.4166   0.0475
   3.000   0.8512   0.01000   0.00315  -0.0900   0.4034   0.0659
   3.250   0.8788   0.01038   0.00345  -0.0900   0.3915   0.0720
   3.500   0.9064   0.01053   0.00357  -0.0900   0.3811   0.0758
   3.750   0.9338   0.01107   0.00403  -0.0899   0.3703   0.0818
   4.000   0.9602   0.01079   0.00374  -0.0899   0.3578   0.0827
   4.250   0.9873   0.01099   0.00391  -0.0898   0.3472   0.0861
   4.500   1.0141   0.01129   0.00416  -0.0897   0.3390   0.0863
   4.750   1.0410   0.01137   0.00424  -0.0897   0.3316   0.0864
   5.000   1.0673   0.01114   0.00404  -0.0897   0.3236   0.0867
   5.250   1.0943   0.01103   0.00399  -0.0897   0.3172   0.0872
   5.500   1.1205   0.01109   0.00405  -0.0896   0.3086   0.0880
   5.750   1.1471   0.01115   0.00413  -0.0896   0.2998   0.0891
   6.250   1.1993   0.01167   0.00458  -0.0893   0.2808   0.0911
   6.500   1.2250   0.01162   0.00456  -0.0892   0.2678   0.0918
   6.750   1.2498   0.01182   0.00470  -0.0890   0.2478   0.0931
   7.000   1.2734   0.01227   0.00502  -0.0885   0.2240   0.0956
   7.250   1.2965   0.01261   0.00525  -0.0880   0.1978   0.0971
   7.750   1.3418   0.01348   0.00595  -0.0869   0.1604   0.1025
   8.250   1.3887   0.01416   0.00658  -0.0859   0.1412   0.1105
   8.500   1.4122   0.01442   0.00684  -0.0854   0.1323   0.1170
  10.000   1.5323   0.01756   0.00960  -0.0796   0.0604   0.1558
  10.250   1.5489   0.01821   0.01023  -0.0782   0.0532   0.1580
  10.500   1.5653   0.01883   0.01084  -0.0766   0.0455   0.1611
  10.750   1.5655   0.02009   0.01194  -0.0725   0.0225   0.1631
  11.000   1.5723   0.02116   0.01302  -0.0696   0.0172   0.1657
  11.250   1.5836   0.02201   0.01395  -0.0675   0.0154   0.1785
  11.500   1.5965   0.02278   0.01482  -0.0658   0.0148   0.1929
  11.750   1.6077   0.02368   0.01580  -0.0640   0.0141   0.1977
  12.000   1.6174   0.02474   0.01694  -0.0621   0.0136   0.2014
  12.250   1.6251   0.02597   0.01826  -0.0602   0.0130   0.2067
  12.500   1.6307   0.02743   0.01981  -0.0582   0.0125   0.2030
  12.750   1.6354   0.02902   0.02149  -0.0563   0.0121   0.1976
  13.000   1.6438   0.03037   0.02291  -0.0550   0.0119   0.1763
  13.250   1.6508   0.03189   0.02450  -0.0536   0.0117   0.1664
  13.500   1.6567   0.03356   0.02626  -0.0524   0.0114   0.1661
  13.750   1.6615   0.03541   0.02819  -0.0513   0.0111   0.1650
  14.000   1.6646   0.03747   0.03034  -0.0502   0.0108   0.1649
  14.250   1.6662   0.03978   0.03274  -0.0493   0.0105   0.1662
  14.500   1.6663   0.04234   0.03540  -0.0486   0.0103   0.1679
  14.750   1.6641   0.04524   0.03841  -0.0480   0.0101   0.1685
  15.000   1.6592   0.04859   0.04186  -0.0476   0.0099   0.1660
  15.250   1.6516   0.05243   0.04582  -0.0476   0.0098   0.1653
  15.500   1.6402   0.05694   0.05046  -0.0478   0.0096   0.1642
  15.750   1.6255   0.06213   0.05579  -0.0485   0.0095   0.1640
  16.000   1.6083   0.06782   0.06162  -0.0495   0.0094   0.1638
  16.250   1.5959   0.07297   0.06689  -0.0505   0.0093   0.1634
  16.500   1.5886   0.07746   0.07149  -0.0515   0.0092   0.1628
  16.750   1.5786   0.08240   0.07653  -0.0527   0.0092   0.1627
  17.000   1.5677   0.08753   0.08178  -0.0540   0.0091   0.1629
  17.250   1.5564   0.09284   0.08719  -0.0555   0.0091   0.1626
  17.500   1.5444   0.09830   0.09277  -0.0572   0.0090   0.1628
  17.750   1.5314   0.10399   0.09857  -0.0590   0.0090   0.1617
  18.000   1.5192   0.10965   0.10433  -0.0609   0.0089   0.1624
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