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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 500,000
Max Cl/Cd: 79.78 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe177-il-500000-n5.txt
Download as CSV file: xf-goe177-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3227   0.10203   0.09990  -0.0184   1.0000   0.0066
  -8.250  -0.3167   0.09873   0.09663  -0.0198   1.0000   0.0066
  -8.000  -0.3159   0.09447   0.09241  -0.0209   1.0000   0.0068
  -7.750  -0.3082   0.09235   0.09031  -0.0210   1.0000   0.0073
  -7.500  -0.3024   0.09007   0.08805  -0.0216   1.0000   0.0078
  -7.250  -0.2985   0.08766   0.08569  -0.0222   0.9990   0.0085
  -7.000  -0.2778   0.08379   0.08181  -0.0284   0.9875   0.0099
  -6.750  -0.2514   0.08015   0.07817  -0.0355   0.9755   0.0106
  -6.500  -0.2292   0.07584   0.07384  -0.0416   0.9600   0.0107
  -6.000  -0.1965   0.06336   0.06126  -0.0538   0.9153   0.0062
  -5.750  -0.1759   0.05902   0.05677  -0.0587   0.8722   0.0059
  -5.500  -0.1529   0.05448   0.05201  -0.0638   0.8270   0.0057
  -5.250  -0.1252   0.04932   0.04662  -0.0699   0.7933   0.0055
  -4.750  -0.0392   0.01953   0.01532  -0.0937   0.7607   0.0049
  -4.500  -0.0109   0.01633   0.01142  -0.0946   0.7394   0.0052
  -4.250   0.0171   0.01457   0.00916  -0.0948   0.7188   0.0056
  -4.000   0.0451   0.01343   0.00761  -0.0948   0.7006   0.0060
  -3.750   0.0729   0.01274   0.00663  -0.0948   0.6831   0.0067
  -3.500   0.1008   0.01176   0.00538  -0.0949   0.6661   0.0075
  -3.250   0.1288   0.01121   0.00462  -0.0948   0.6490   0.0081
  -3.000   0.1569   0.01076   0.00398  -0.0947   0.6337   0.0091
  -2.750   0.1851   0.01041   0.00344  -0.0946   0.6180   0.0102
  -2.500   0.2132   0.01004   0.00287  -0.0946   0.6011   0.0134
  -2.250   0.2411   0.00981   0.00249  -0.0944   0.5818   0.0182
  -2.000   0.2690   0.00961   0.00220  -0.0944   0.5635   0.0325
  -1.750   0.2967   0.00953   0.00216  -0.0944   0.5458   0.0590
  -1.500   0.3244   0.00961   0.00212  -0.0943   0.5293   0.0696
  -1.250   0.3522   0.00968   0.00210  -0.0942   0.5148   0.0787
  -1.000   0.3801   0.00972   0.00202  -0.0942   0.5016   0.0810
  -0.750   0.4080   0.00965   0.00187  -0.0942   0.4889   0.0841
  -0.500   0.4356   0.00967   0.00178  -0.0941   0.4697   0.0872
  -0.250   0.4631   0.00973   0.00172  -0.0941   0.4492   0.0908
   0.000   0.4906   0.00980   0.00167  -0.0940   0.4277   0.0930
   0.250   0.5180   0.00989   0.00164  -0.0939   0.4086   0.0949
   0.500   0.5453   0.00998   0.00163  -0.0939   0.3851   0.0996
   0.750   0.5724   0.01011   0.00165  -0.0938   0.3617   0.1070
   1.000   0.5998   0.01020   0.00169  -0.0938   0.3447   0.1227
   1.250   0.6272   0.01019   0.00176  -0.0939   0.3312   0.1783
   1.500   0.6546   0.01019   0.00187  -0.0939   0.3178   0.2528
   1.750   0.6818   0.01024   0.00199  -0.0940   0.3029   0.3194
   2.000   0.7089   0.01029   0.00211  -0.0940   0.2859   0.3874
   2.500   0.7555   0.00947   0.00237  -0.0923   0.2434   1.0000
   2.750   0.7794   0.01021   0.00270  -0.0920   0.1684   1.0000
   3.000   0.8035   0.01093   0.00311  -0.0916   0.1100   1.0000
   3.250   0.8302   0.01117   0.00331  -0.0915   0.1011   1.0000
   3.500   0.8570   0.01139   0.00349  -0.0914   0.0935   1.0000
   3.750   0.8821   0.01190   0.00383  -0.0911   0.0577   1.0000
   4.000   0.9086   0.01215   0.00407  -0.0909   0.0525   1.0000
   4.250   0.9352   0.01237   0.00431  -0.0908   0.0496   1.0000
   4.500   0.9617   0.01260   0.00456  -0.0907   0.0461   1.0000
   4.750   0.9876   0.01291   0.00485  -0.0905   0.0398   1.0000
   5.000   1.0124   0.01339   0.00515  -0.0901   0.0176   1.0000
   5.250   1.0387   0.01362   0.00548  -0.0899   0.0124   1.0000
   5.500   1.0642   0.01398   0.00595  -0.0896   0.0101   1.0000
   5.750   1.0889   0.01447   0.00657  -0.0891   0.0085   1.0000
   6.000   1.1133   0.01496   0.00714  -0.0886   0.0072   1.0000
   6.250   1.1376   0.01544   0.00772  -0.0881   0.0062   1.0000
   6.500   1.1610   0.01603   0.00839  -0.0875   0.0056   1.0000
   6.750   1.1818   0.01695   0.00943  -0.0865   0.0051   1.0000
   7.000   1.2034   0.01771   0.01028  -0.0856   0.0049   1.0000
   7.250   1.2251   0.01841   0.01106  -0.0848   0.0043   1.0000
   7.500   1.2460   0.01913   0.01184  -0.0840   0.0038   1.0000
   7.750   1.2644   0.02010   0.01292  -0.0828   0.0035   1.0000
   8.000   1.2779   0.02151   0.01443  -0.0809   0.0033   1.0000
   8.250   1.2917   0.02278   0.01582  -0.0790   0.0032   1.0000
   8.500   1.3037   0.02415   0.01730  -0.0768   0.0030   1.0000
   8.750   1.3133   0.02566   0.01891  -0.0744   0.0029   1.0000
   9.000   1.3205   0.02724   0.02060  -0.0716   0.0028   1.0000
   9.250   1.3251   0.02885   0.02231  -0.0685   0.0028   1.0000
   9.500   1.3300   0.03060   0.02416  -0.0656   0.0028   1.0000
   9.750   1.3359   0.03246   0.02613  -0.0631   0.0027   1.0000
  10.000   1.3427   0.03443   0.02822  -0.0608   0.0027   1.0000
  10.250   1.3499   0.03645   0.03038  -0.0587   0.0027   1.0000
  10.500   1.3564   0.03844   0.03252  -0.0568   0.0025   1.0000
  10.750   1.3616   0.04047   0.03468  -0.0552   0.0024   1.0000
  11.000   1.3656   0.04259   0.03692  -0.0538   0.0022   1.0000
  11.250   1.3686   0.04480   0.03924  -0.0527   0.0021   1.0000
  11.500   1.3700   0.04729   0.04185  -0.0519   0.0021   1.0000
  11.750   1.3693   0.05021   0.04490  -0.0511   0.0020   1.0000
  12.000   1.3658   0.05383   0.04868  -0.0501   0.0019   1.0000
  12.250   1.3611   0.05756   0.05267  -0.0496   0.0019   1.0000
  12.500   1.3549   0.06149   0.05683  -0.0496   0.0019   1.0000
  12.750   1.3470   0.06581   0.06136  -0.0500   0.0019   1.0000
  13.000   1.3373   0.07048   0.06623  -0.0507   0.0018   1.0000
  13.250   1.3263   0.07549   0.07144  -0.0519   0.0018   1.0000
  13.500   1.3145   0.08072   0.07685  -0.0534   0.0018   1.0000
  13.750   1.3010   0.08644   0.08275  -0.0554   0.0018   1.0000
  14.000   1.2873   0.09246   0.08895  -0.0578   0.0018   1.0000
  14.250   1.2732   0.09878   0.09544  -0.0606   0.0018   1.0000
  14.500   1.2595   0.10530   0.10210  -0.0637   0.0018   1.0000
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