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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 200,000
Max Cl/Cd: 76.28 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802b-il-200000.txt
Download as CSV file: xf-goe802b-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3036   0.10223   0.09891  -0.0316   1.0000   0.0352
  -8.250  -0.3270   0.10230   0.09908  -0.0273   1.0000   0.0352
  -8.000  -0.3451   0.10177   0.09863  -0.0254   1.0000   0.0352
  -7.750  -0.3416   0.09790   0.09480  -0.0231   0.9994   0.0354
  -7.500  -0.3238   0.09329   0.09018  -0.0238   0.9969   0.0359
  -7.250  -0.2992   0.08888   0.08576  -0.0291   0.9931   0.0367
  -7.000  -0.2751   0.08475   0.08160  -0.0351   0.9871   0.0377
  -6.750  -0.2454   0.08034   0.07715  -0.0430   0.9823   0.0393
  -6.500  -0.1926   0.07570   0.07226  -0.0640   0.9722   0.0413
  -6.250  -0.1767   0.07091   0.06756  -0.0630   0.9696   0.0417
  -6.000  -0.1492   0.06680   0.06344  -0.0668   0.9669   0.0425
  -5.750  -0.1219   0.06328   0.05986  -0.0713   0.9604   0.0437
  -5.500  -0.0862   0.05942   0.05590  -0.0778   0.9552   0.0458
  -5.250  -0.0338   0.05520   0.05136  -0.0885   0.9508   0.0479
  -5.000  -0.0147   0.05180   0.04801  -0.0894   0.9434   0.0486
  -4.750   0.0134   0.04888   0.04502  -0.0921   0.9369   0.0504
  -4.250   0.0794   0.04360   0.03929  -0.0980   0.9212   0.0546
  -4.000   0.1040   0.04065   0.03631  -0.0991   0.9148   0.0556
  -3.750   0.1258   0.03859   0.03415  -0.0991   0.9033   0.0573
  -3.500   0.1631   0.03863   0.03355  -0.0998   0.8950   0.0607
  -3.250   0.1805   0.03484   0.02991  -0.0995   0.8837   0.0613
  -3.000   0.2032   0.03265   0.02764  -0.0994   0.8746   0.0628
  -2.750   0.2290   0.03122   0.02601  -0.0990   0.8641   0.0658
  -2.500   0.2555   0.02976   0.02430  -0.0987   0.8540   0.0677
  -2.250   0.2801   0.02802   0.02244  -0.0984   0.8439   0.0698
  -2.000   0.3099   0.02859   0.02254  -0.0974   0.8316   0.0724
  -1.750   0.3340   0.02584   0.01976  -0.0973   0.8216   0.0731
  -1.500   0.3595   0.02431   0.01810  -0.0970   0.8090   0.0746
  -1.250   0.3870   0.02367   0.01722  -0.0964   0.7962   0.0767
  -1.000   0.4164   0.02433   0.01743  -0.0954   0.7841   0.0773
  -0.750   0.4417   0.02180   0.01490  -0.0954   0.7713   0.0779
  -0.500   0.4683   0.02060   0.01357  -0.0951   0.7569   0.0793
  -0.250   0.4962   0.02045   0.01316  -0.0945   0.7420   0.0815
   0.000   0.5241   0.02040   0.01284  -0.0938   0.7268   0.0818
   0.250   0.5515   0.02003   0.01224  -0.0933   0.7117   0.0819
   0.500   0.5788   0.01945   0.01147  -0.0928   0.6967   0.0819
   0.750   0.6058   0.01882   0.01068  -0.0924   0.6811   0.0819
   1.000   0.6327   0.01818   0.00991  -0.0921   0.6650   0.0818
   1.500   0.6865   0.01716   0.00864  -0.0913   0.6338   0.0818
   1.750   0.7131   0.01647   0.00787  -0.0911   0.6194   0.0855
   2.000   0.7401   0.01662   0.00783  -0.0906   0.6054   0.0865
   2.250   0.7667   0.01617   0.00728  -0.0903   0.5918   0.0907
   2.500   0.7931   0.01564   0.00672  -0.0900   0.5776   0.0982
   2.750   0.8180   0.01411   0.00543  -0.0897   0.5647   0.1312
   3.000   0.8427   0.01187   0.00507  -0.0893   0.5527   1.0000
   3.250   0.8687   0.01212   0.00516  -0.0889   0.5387   1.0000
   3.500   0.8943   0.01235   0.00530  -0.0885   0.5239   1.0000
   3.750   0.9200   0.01261   0.00545  -0.0881   0.5099   1.0000
   4.000   0.9455   0.01288   0.00562  -0.0877   0.4971   1.0000
   4.250   0.9711   0.01315   0.00578  -0.0873   0.4846   1.0000
   4.500   0.9967   0.01339   0.00601  -0.0870   0.4726   1.0000
   4.750   1.0223   0.01371   0.00624  -0.0867   0.4629   1.0000
   5.000   1.0479   0.01396   0.00649  -0.0864   0.4523   1.0000
   5.250   1.0733   0.01426   0.00674  -0.0861   0.4427   1.0000
   5.500   1.0985   0.01453   0.00699  -0.0857   0.4325   1.0000
   5.750   1.1236   0.01483   0.00729  -0.0853   0.4228   1.0000
   6.000   1.1484   0.01513   0.00754  -0.0849   0.4131   1.0000
   6.250   1.1729   0.01540   0.00785  -0.0845   0.4024   1.0000
   6.500   1.1972   0.01575   0.00813  -0.0840   0.3926   1.0000
   6.750   1.2212   0.01601   0.00846  -0.0835   0.3816   1.0000
   7.000   1.2447   0.01634   0.00879  -0.0829   0.3707   1.0000
   7.250   1.2675   0.01671   0.00908  -0.0822   0.3590   1.0000
   7.500   1.2900   0.01699   0.00944  -0.0815   0.3459   1.0000
   7.750   1.3123   0.01735   0.00984  -0.0807   0.3337   1.0000
   8.000   1.3337   0.01777   0.01023  -0.0798   0.3213   1.0000
   8.250   1.3544   0.01819   0.01065  -0.0789   0.3074   1.0000
   8.500   1.3747   0.01860   0.01110  -0.0778   0.2922   1.0000
   8.750   1.3936   0.01907   0.01159  -0.0766   0.2753   1.0000
   9.000   1.4112   0.01961   0.01211  -0.0753   0.2570   1.0000
   9.250   1.4273   0.02025   0.01268  -0.0737   0.2389   1.0000
   9.500   1.4428   0.02094   0.01334  -0.0721   0.2220   1.0000
   9.750   1.4570   0.02171   0.01408  -0.0703   0.2072   1.0000
  10.000   1.4700   0.02251   0.01487  -0.0684   0.1940   1.0000
  10.250   1.4804   0.02335   0.01571  -0.0661   0.1831   1.0000
  10.500   1.4879   0.02442   0.01671  -0.0635   0.1740   1.0000
  10.750   1.4999   0.02529   0.01767  -0.0617   0.1652   1.0000
  11.000   1.5066   0.02652   0.01886  -0.0594   0.1576   1.0000
  11.250   1.5182   0.02747   0.01994  -0.0578   0.1495   1.0000
  11.750   1.5353   0.02989   0.02248  -0.0543   0.1357   1.0000
  12.000   1.5418   0.03132   0.02393  -0.0526   0.1298   1.0000
  12.250   1.5498   0.03269   0.02540  -0.0511   0.1239   1.0000
  12.500   1.5581   0.03407   0.02689  -0.0499   0.1176   1.0000
  12.750   1.5609   0.03597   0.02878  -0.0485   0.1125   1.0000
  13.000   1.5715   0.03727   0.03027  -0.0476   0.1066   1.0000
  13.250   1.5759   0.03917   0.03221  -0.0466   0.1009   1.0000
  13.500   1.5814   0.04104   0.03419  -0.0458   0.0951   1.0000
  13.750   1.5846   0.04322   0.03642  -0.0451   0.0875   1.0000
  14.000   1.5872   0.04553   0.03883  -0.0444   0.0813   1.0000
  14.250   1.5856   0.04839   0.04174  -0.0440   0.0747   1.0000
  14.500   1.5831   0.05144   0.04487  -0.0436   0.0681   1.0000
  14.750   1.5744   0.05534   0.04879  -0.0436   0.0625   1.0000
  15.000   1.5695   0.05895   0.05252  -0.0436   0.0561   1.0000
  15.250   1.5585   0.06349   0.05712  -0.0441   0.0511   1.0000
  15.500   1.5503   0.06780   0.06153  -0.0447   0.0449   1.0000
  15.750   1.5395   0.07261   0.06643  -0.0456   0.0403   1.0000
  16.000   1.5278   0.07766   0.07157  -0.0467   0.0365   1.0000
  16.250   1.5148   0.08304   0.07703  -0.0480   0.0342   1.0000
  16.500   1.5024   0.08845   0.08255  -0.0495   0.0324   1.0000
  16.750   1.4891   0.09410   0.08831  -0.0512   0.0312   1.0000
  17.000   1.4747   0.10001   0.09433  -0.0531   0.0302   1.0000
  17.250   1.4599   0.10615   0.10057  -0.0553   0.0294   1.0000
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