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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 200,000
Max Cl/Cd: 71.51 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe177-il-200000-n5.txt
Download as CSV file: xf-goe177-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3035   0.09626   0.09312  -0.0247   1.0000   0.0206
  -7.250  -0.3013   0.09352   0.09044  -0.0253   1.0000   0.0207
  -7.000  -0.2979   0.09066   0.08763  -0.0263   1.0000   0.0207
  -6.750  -0.2945   0.08779   0.08482  -0.0272   1.0000   0.0207
  -6.500  -0.2911   0.08493   0.08201  -0.0279   1.0000   0.0207
  -6.250  -0.1815   0.05856   0.05579  -0.0389   0.9709   0.0167
  -6.000  -0.1660   0.05324   0.05046  -0.0444   0.9591   0.0149
  -5.750  -0.2240   0.06931   0.06636  -0.0427   0.9807   0.0159
  -5.500  -0.1889   0.06236   0.05935  -0.0534   0.9703   0.0131
  -5.250  -0.1471   0.05463   0.05151  -0.0646   0.9589   0.0113
  -5.000  -0.1124   0.04910   0.04584  -0.0722   0.9464   0.0118
  -4.750  -0.0804   0.04600   0.04263  -0.0768   0.9306   0.0134
  -4.500  -0.0417   0.04024   0.03665  -0.0835   0.9122   0.0136
  -4.250   0.0014   0.03129   0.02725  -0.0910   0.8919   0.0128
  -4.000   0.0429   0.02114   0.01598  -0.0964   0.8724   0.0124
  -3.750   0.0755   0.01789   0.01197  -0.0975   0.8457   0.0129
  -3.500   0.1052   0.01605   0.00957  -0.0976   0.8182   0.0139
  -3.250   0.1332   0.01507   0.00819  -0.0973   0.7917   0.0163
  -3.000   0.1609   0.01410   0.00681  -0.0969   0.7677   0.0186
  -2.750   0.1886   0.01335   0.00570  -0.0964   0.7457   0.0205
  -2.500   0.2159   0.01266   0.00481  -0.0961   0.7255   0.0275
  -2.250   0.2435   0.01217   0.00420  -0.0958   0.7064   0.0418
  -2.000   0.2708   0.01228   0.00418  -0.0954   0.6879   0.0679
  -1.750   0.2980   0.01238   0.00411  -0.0952   0.6702   0.0847
  -1.500   0.3252   0.01233   0.00387  -0.0949   0.6535   0.0940
  -1.250   0.3524   0.01214   0.00357  -0.0947   0.6373   0.0998
  -1.000   0.3796   0.01209   0.00338  -0.0945   0.6211   0.1077
  -0.750   0.4069   0.01198   0.00318  -0.0943   0.6054   0.1129
  -0.500   0.4341   0.01192   0.00300  -0.0942   0.5904   0.1174
  -0.250   0.4615   0.01190   0.00287  -0.0940   0.5763   0.1231
   0.000   0.4887   0.01185   0.00278  -0.0938   0.5621   0.1334
   0.250   0.5159   0.01182   0.00271  -0.0937   0.5475   0.1521
   0.500   0.5429   0.01172   0.00271  -0.0936   0.5327   0.2064
   0.750   0.5697   0.01160   0.00276  -0.0935   0.5177   0.3035
   1.000   0.5961   0.01150   0.00278  -0.0934   0.5001   0.3953
   1.250   0.6171   0.01038   0.00275  -0.0915   0.4812   1.0000
   1.500   0.6437   0.01058   0.00276  -0.0913   0.4602   1.0000
   1.750   0.6702   0.01079   0.00281  -0.0911   0.4403   1.0000
   2.250   0.7232   0.01124   0.00295  -0.0906   0.4035   1.0000
   2.500   0.7495   0.01147   0.00306  -0.0904   0.3851   1.0000
   2.750   0.7758   0.01172   0.00318  -0.0902   0.3690   1.0000
   3.000   0.8024   0.01193   0.00333  -0.0900   0.3574   1.0000
   3.250   0.8289   0.01216   0.00351  -0.0898   0.3468   1.0000
   3.500   0.8552   0.01240   0.00369  -0.0896   0.3364   1.0000
   3.750   0.8818   0.01261   0.00389  -0.0895   0.3268   1.0000
   4.000   0.9081   0.01285   0.00411  -0.0893   0.3182   1.0000
   4.250   0.9345   0.01307   0.00436  -0.0891   0.3101   1.0000
   4.500   0.9597   0.01342   0.00461  -0.0888   0.2867   1.0000
   4.750   0.9839   0.01391   0.00490  -0.0885   0.2495   1.0000
   5.000   0.9992   0.01573   0.00586  -0.0873   0.1131   1.0000
   5.250   1.0202   0.01675   0.00664  -0.0865   0.0584   1.0000
   5.500   1.0444   0.01725   0.00715  -0.0861   0.0489   1.0000
   5.750   1.0689   0.01769   0.00765  -0.0856   0.0363   1.0000
   6.000   1.0912   0.01844   0.00835  -0.0849   0.0168   1.0000
   6.250   1.1149   0.01897   0.00909  -0.0842   0.0135   1.0000
   6.500   1.1381   0.01956   0.00986  -0.0834   0.0124   1.0000
   6.750   1.1601   0.02026   0.01075  -0.0826   0.0115   1.0000
   7.000   1.1805   0.02113   0.01181  -0.0815   0.0100   1.0000
   7.250   1.1993   0.02214   0.01301  -0.0803   0.0093   1.0000
   7.500   1.2157   0.02335   0.01441  -0.0787   0.0088   1.0000
   7.750   1.2284   0.02482   0.01607  -0.0768   0.0085   1.0000
   8.000   1.2366   0.02659   0.01797  -0.0745   0.0082   1.0000
   8.250   1.2406   0.02857   0.02011  -0.0716   0.0081   1.0000
   8.750   1.2528   0.03168   0.02343  -0.0663   0.0074   1.0000
   9.000   1.2626   0.03291   0.02480  -0.0643   0.0068   1.0000
   9.250   1.2675   0.03465   0.02666  -0.0620   0.0065   1.0000
   9.500   1.2717   0.03664   0.02874  -0.0598   0.0064   1.0000
   9.750   1.2768   0.03870   0.03091  -0.0579   0.0063   1.0000
  10.000   1.2831   0.04083   0.03315  -0.0561   0.0062   1.0000
  10.250   1.2906   0.04301   0.03544  -0.0545   0.0061   1.0000
  10.500   1.2989   0.04527   0.03783  -0.0529   0.0061   1.0000
  10.750   1.3072   0.04765   0.04037  -0.0513   0.0061   1.0000
  11.000   1.3143   0.05022   0.04312  -0.0499   0.0061   1.0000
  11.250   1.3192   0.05304   0.04615  -0.0486   0.0062   1.0000
  11.500   1.3215   0.05615   0.04949  -0.0474   0.0063   1.0000
  11.750   1.3212   0.05953   0.05309  -0.0465   0.0064   1.0000
  12.000   1.3183   0.06321   0.05701  -0.0459   0.0065   1.0000
  12.250   1.3130   0.06721   0.06124  -0.0457   0.0066   1.0000
  12.500   1.3055   0.07152   0.06578  -0.0458   0.0067   1.0000
  12.750   1.2963   0.07615   0.07063  -0.0464   0.0068   1.0000
  13.000   1.2855   0.08109   0.07578  -0.0474   0.0069   1.0000
  13.250   1.2736   0.08632   0.08121  -0.0489   0.0070   1.0000
  13.500   1.2610   0.09180   0.08688  -0.0507   0.0071   1.0000
  13.750   1.2474   0.09760   0.09286  -0.0529   0.0072   1.0000
  14.000   1.2337   0.10364   0.09907  -0.0554   0.0073   1.0000
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