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GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 766 AIRFOIL (goe766-il)
Reynolds number: 50,000
Max Cl/Cd: 27.37 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe766-il-50000-n5.txt
Download as CSV file: xf-goe766-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 766 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6570   0.08049   0.07251  -0.0268   1.0000   0.0778
 -10.250  -0.6825   0.07445   0.06642  -0.0296   1.0000   0.0775
 -10.000  -0.7080   0.06968   0.06156  -0.0297   1.0000   0.0773
  -9.750  -0.7296   0.06533   0.05704  -0.0286   1.0000   0.0774
  -9.500  -0.7474   0.06097   0.05239  -0.0272   1.0000   0.0777
  -9.250  -0.7556   0.05720   0.04835  -0.0256   1.0000   0.0784
  -9.000  -0.7456   0.05501   0.04612  -0.0245   1.0000   0.0798
  -8.750  -0.7386   0.05254   0.04352  -0.0230   1.0000   0.0810
  -8.500  -0.7331   0.04974   0.04048  -0.0214   1.0000   0.0821
  -8.250  -0.7262   0.04689   0.03734  -0.0197   1.0000   0.0831
  -8.000  -0.7170   0.04418   0.03432  -0.0180   1.0000   0.0843
  -7.750  -0.7056   0.04172   0.03151  -0.0162   1.0000   0.0863
  -7.500  -0.6930   0.03933   0.02867  -0.0144   1.0000   0.0886
  -7.250  -0.6761   0.03742   0.02656  -0.0130   1.0000   0.0908
  -7.000  -0.6568   0.03590   0.02499  -0.0118   1.0000   0.0930
  -6.750  -0.6372   0.03430   0.02324  -0.0106   1.0000   0.0953
  -6.500  -0.6169   0.03277   0.02149  -0.0093   1.0000   0.0987
  -6.250  -0.5959   0.03136   0.01989  -0.0080   1.0000   0.1026
  -6.000  -0.5748   0.03028   0.01887  -0.0069   1.0000   0.1066
  -5.750  -0.5524   0.02911   0.01758  -0.0057   1.0000   0.1112
  -5.500  -0.5301   0.02803   0.01647  -0.0046   1.0000   0.1168
  -5.250  -0.5085   0.02714   0.01559  -0.0034   1.0000   0.1238
  -5.000  -0.4864   0.02619   0.01465  -0.0022   1.0000   0.1316
  -4.750  -0.4646   0.02536   0.01376  -0.0009   1.0000   0.1427
  -4.500  -0.4441   0.02448   0.01302   0.0004   1.0000   0.1554
  -4.250  -0.4239   0.02363   0.01226   0.0017   1.0000   0.1724
  -4.000  -0.4045   0.02279   0.01155   0.0031   1.0000   0.1943
  -3.750  -0.3867   0.02195   0.01094   0.0047   1.0000   0.2221
  -3.500  -0.3695   0.02114   0.01042   0.0062   1.0000   0.2590
  -3.250  -0.3552   0.02032   0.01005   0.0082   1.0000   0.3134
  -3.000  -0.3440   0.01951   0.00984   0.0109   1.0000   0.4020
  -2.750  -0.3253   0.01870   0.01001   0.0128   0.9921   0.5549
  -2.500  -0.2794   0.01852   0.01039   0.0112   0.9697   0.7089
  -2.250  -0.2244   0.01868   0.01063   0.0079   0.9455   0.7874
  -2.000  -0.1624   0.01890   0.01074   0.0031   0.9183   0.8378
  -1.750  -0.0981   0.01910   0.01075  -0.0023   0.8844   0.8735
  -1.500  -0.0117   0.01953   0.01091  -0.0109   0.8412   0.9137
  -1.250   0.0612   0.01971   0.01071  -0.0177   0.7857   0.9429
  -1.000   0.1106   0.01970   0.01030  -0.0211   0.7350   0.9583
  -0.750   0.1526   0.01970   0.00994  -0.0235   0.6940   0.9718
  -0.500   0.1945   0.01969   0.00960  -0.0262   0.6591   0.9849
  -0.250   0.2381   0.01963   0.00926  -0.0295   0.6287   0.9987
   0.000   0.2594   0.01969   0.00911  -0.0287   0.6066   1.0000
   0.250   0.2784   0.01977   0.00903  -0.0274   0.5864   1.0000
   0.500   0.2979   0.01987   0.00899  -0.0261   0.5680   1.0000
   0.750   0.3177   0.02000   0.00898  -0.0249   0.5513   1.0000
   1.000   0.3377   0.02017   0.00901  -0.0236   0.5358   1.0000
   1.250   0.3578   0.02035   0.00910  -0.0223   0.5206   1.0000
   1.500   0.3782   0.02057   0.00925  -0.0211   0.5061   1.0000
   1.750   0.3989   0.02081   0.00943  -0.0200   0.4925   1.0000
   2.000   0.4204   0.02109   0.00961  -0.0189   0.4799   1.0000
   2.250   0.4418   0.02138   0.00984  -0.0178   0.4677   1.0000
   2.500   0.4631   0.02172   0.01017  -0.0167   0.4555   1.0000
   2.750   0.4846   0.02207   0.01044  -0.0156   0.4449   1.0000
   3.000   0.5059   0.02245   0.01081  -0.0144   0.4338   1.0000
   3.250   0.5272   0.02288   0.01123  -0.0133   0.4234   1.0000
   3.500   0.5488   0.02329   0.01160  -0.0121   0.4142   1.0000
   3.750   0.5699   0.02379   0.01215  -0.0110   0.4043   1.0000
   4.000   0.5917   0.02423   0.01253  -0.0099   0.3960   1.0000
   4.250   0.6124   0.02480   0.01319  -0.0088   0.3862   1.0000
   4.500   0.6343   0.02526   0.01360  -0.0076   0.3786   1.0000
   4.750   0.6545   0.02590   0.01437  -0.0065   0.3693   1.0000
   5.000   0.6763   0.02636   0.01479  -0.0053   0.3616   1.0000
   5.250   0.6960   0.02705   0.01561  -0.0041   0.3523   1.0000
   5.500   0.7178   0.02748   0.01601  -0.0029   0.3445   1.0000
   5.750   0.7366   0.02820   0.01688  -0.0015   0.3347   1.0000
   6.000   0.7587   0.02855   0.01716  -0.0003   0.3270   1.0000
   6.250   0.7763   0.02933   0.01815   0.0011   0.3165   1.0000
   6.500   0.7968   0.02980   0.01861   0.0024   0.3079   1.0000
   6.750   0.8154   0.03041   0.01933   0.0038   0.2978   1.0000
   7.000   0.8337   0.03106   0.02007   0.0053   0.2879   1.0000
   7.250   0.8546   0.03137   0.02033   0.0066   0.2785   1.0000
   7.500   0.8702   0.03218   0.02134   0.0082   0.2671   1.0000
   7.750   0.8877   0.03276   0.02197   0.0097   0.2564   1.0000
   8.000   0.9069   0.03313   0.02230   0.0112   0.2461   1.0000
   8.250   0.9202   0.03408   0.02345   0.0129   0.2341   1.0000
   8.500   0.9350   0.03489   0.02434   0.0145   0.2233   1.0000
   8.750   0.9528   0.03532   0.02468   0.0160   0.2134   1.0000
   9.000   0.9621   0.03663   0.02626   0.0179   0.2020   1.0000
   9.250   0.9730   0.03774   0.02748   0.0197   0.1919   1.0000
   9.500   0.9876   0.03842   0.02809   0.0213   0.1832   1.0000
   9.750   0.9915   0.04020   0.03011   0.0233   0.1737   1.0000
  10.000   1.0011   0.04129   0.03120   0.0251   0.1662   1.0000
  10.250   1.0034   0.04307   0.03315   0.0270   0.1588   1.0000
  10.500   1.0108   0.04434   0.03439   0.0287   0.1530   1.0000
  10.750   1.0028   0.04681   0.03707   0.0310   0.1478   1.0000
  11.000   1.0060   0.04825   0.03848   0.0327   0.1430   1.0000
  11.250   1.0001   0.05081   0.04114   0.0339   0.1390   1.0000
  11.500   0.9803   0.05512   0.04566   0.0338   0.1358   1.0000
  11.750   0.9647   0.05957   0.05025   0.0327   0.1328   1.0000
  12.000   0.9838   0.05985   0.05040   0.0340   0.1287   1.0000
  12.250   0.9468   0.06787   0.05866   0.0300   0.1270   1.0000
  12.500   0.7966   0.09877   0.08979   0.0112   0.1249   1.0000
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