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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 100,000
Max Cl/Cd: 60.19 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe124-il-100000.txt
Download as CSV file: xf-goe124-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2843   0.09718   0.09250  -0.0273   1.0000   0.0597
  -7.500  -0.2816   0.09484   0.09023  -0.0275   1.0000   0.0612
  -7.250  -0.2833   0.09298   0.08847  -0.0272   1.0000   0.0627
  -7.000  -0.2898   0.09164   0.08725  -0.0263   1.0000   0.0640
  -6.750  -0.3036   0.09106   0.08679  -0.0242   1.0000   0.0649
  -6.500  -0.3192   0.09078   0.08661  -0.0223   1.0000   0.0657
  -6.250  -0.3311   0.09075   0.08666  -0.0233   1.0000   0.0668
  -6.000  -0.2998   0.08647   0.08231  -0.0363   0.9943   0.0686
  -5.750  -0.2841   0.08163   0.07751  -0.0339   0.9893   0.0708
  -5.500  -0.2501   0.07733   0.07316  -0.0399   0.9833   0.0746
  -5.250  -0.1745   0.07318   0.06864  -0.0651   0.9724   0.0823
  -5.000  -0.1616   0.06801   0.06359  -0.0625   0.9669   0.0842
  -4.750  -0.1326   0.06449   0.06006  -0.0653   0.9597   0.0895
  -4.500  -0.0763   0.05988   0.05523  -0.0787   0.9532   0.0990
  -4.250  -0.0476   0.05668   0.05201  -0.0810   0.9453   0.1046
  -4.000   0.0079   0.05239   0.04752  -0.0917   0.9411   0.1156
  -3.750   0.0521   0.04950   0.04440  -0.0990   0.9320   0.1292
  -3.500   0.0960   0.04639   0.04114  -0.1047   0.9266   0.1448
  -3.250   0.1270   0.04390   0.03861  -0.1073   0.9178   0.1610
  -3.000   0.1625   0.04127   0.03595  -0.1102   0.9114   0.1790
  -2.750   0.1979   0.03949   0.03400  -0.1136   0.9022   0.2069
  -2.500   0.2285   0.03714   0.03168  -0.1148   0.8953   0.2291
  -2.250   0.2565   0.03557   0.03003  -0.1160   0.8848   0.2690
  -1.000   0.4573   0.02527   0.01748  -0.1259   0.8350   0.1408
  -0.750   0.4892   0.02378   0.01562  -0.1256   0.8260   0.1208
  -0.500   0.5202   0.02291   0.01432  -0.1249   0.8172   0.1099
  -0.250   0.5481   0.02207   0.01336  -0.1245   0.8067   0.1065
   0.000   0.5767   0.02137   0.01247  -0.1237   0.7989   0.1073
   0.250   0.6037   0.02087   0.01189  -0.1231   0.7878   0.1071
   0.500   0.6308   0.02039   0.01135  -0.1223   0.7778   0.1064
   0.750   0.6578   0.01988   0.01078  -0.1213   0.7693   0.1070
   1.000   0.6839   0.01963   0.01054  -0.1206   0.7580   0.1089
   1.250   0.7105   0.01941   0.01026  -0.1197   0.7481   0.1124
   1.500   0.7379   0.01908   0.00990  -0.1189   0.7386   0.1243
   2.000   0.7845   0.01724   0.00985  -0.1161   0.7162   1.0000
   2.250   0.8122   0.01732   0.00958  -0.1151   0.7067   1.0000
   2.500   0.8385   0.01758   0.00968  -0.1145   0.6939   1.0000
   2.750   0.8649   0.01781   0.00980  -0.1139   0.6815   1.0000
   3.000   0.8915   0.01801   0.00991  -0.1133   0.6694   1.0000
   3.250   0.9185   0.01815   0.00992  -0.1126   0.6580   1.0000
   3.500   0.9451   0.01835   0.01003  -0.1120   0.6454   1.0000
   3.750   0.9713   0.01864   0.01030  -0.1115   0.6318   1.0000
   4.000   0.9975   0.01896   0.01060  -0.1110   0.6187   1.0000
   4.250   1.0238   0.01926   0.01088  -0.1105   0.6059   1.0000
   4.500   1.0501   0.01949   0.01106  -0.1099   0.5929   1.0000
   4.750   1.0766   0.01967   0.01119  -0.1093   0.5801   1.0000
   5.000   1.1032   0.01983   0.01129  -0.1087   0.5676   1.0000
   5.250   1.1286   0.02014   0.01164  -0.1082   0.5541   1.0000
   5.500   1.1541   0.02049   0.01205  -0.1077   0.5415   1.0000
   5.750   1.1798   0.02079   0.01238  -0.1072   0.5295   1.0000
   6.000   1.2059   0.02104   0.01262  -0.1066   0.5183   1.0000
   6.250   1.2319   0.02131   0.01293  -0.1061   0.5074   1.0000
   6.500   1.2565   0.02163   0.01335  -0.1055   0.4946   1.0000
   6.750   1.2811   0.02188   0.01368  -0.1048   0.4815   1.0000
   7.000   1.3059   0.02219   0.01405  -0.1042   0.4693   1.0000
   7.250   1.3307   0.02247   0.01441  -0.1035   0.4571   1.0000
   7.500   1.3549   0.02272   0.01472  -0.1027   0.4435   1.0000
   7.750   1.3780   0.02300   0.01509  -0.1018   0.4281   1.0000
   8.000   1.3999   0.02330   0.01551  -0.1007   0.4107   1.0000
   8.250   1.4206   0.02360   0.01592  -0.0994   0.3904   1.0000
   8.500   1.4396   0.02398   0.01635  -0.0978   0.3662   1.0000
   8.750   1.4546   0.02452   0.01691  -0.0957   0.3339   1.0000
   9.000   1.4653   0.02534   0.01762  -0.0932   0.2947   1.0000
   9.250   1.4731   0.02640   0.01859  -0.0905   0.2505   1.0000
   9.500   1.4799   0.02772   0.01976  -0.0880   0.2126   1.0000
   9.750   1.4844   0.02934   0.02118  -0.0853   0.1874   1.0000
  10.000   1.4871   0.03113   0.02283  -0.0824   0.1701   1.0000
  10.250   1.4865   0.03298   0.02462  -0.0791   0.1560   1.0000
  10.500   1.4855   0.03504   0.02665  -0.0760   0.1423   1.0000
  10.750   1.4830   0.03736   0.02897  -0.0733   0.1283   1.0000
  11.000   1.4781   0.04004   0.03161  -0.0707   0.1134   1.0000
  11.250   1.4717   0.04302   0.03452  -0.0683   0.0985   1.0000
  11.500   1.4668   0.04598   0.03752  -0.0664   0.0858   1.0000
  11.750   1.4665   0.04876   0.04038  -0.0646   0.0762   1.0000
  12.000   1.4700   0.05135   0.04296  -0.0629   0.0697   1.0000
  12.250   1.4731   0.05384   0.04553  -0.0616   0.0645   1.0000
  12.500   1.4800   0.05628   0.04793  -0.0601   0.0602   1.0000
  12.750   1.4852   0.05891   0.05081  -0.0588   0.0568   1.0000
  13.000   1.4931   0.06136   0.05335  -0.0575   0.0541   1.0000
  13.250   1.5146   0.06379   0.05566  -0.0558   0.0512   1.0000
  13.500   1.5126   0.06720   0.05944  -0.0547   0.0502   1.0000
  13.750   1.5085   0.07093   0.06351  -0.0538   0.0491   1.0000
  14.000   1.5017   0.07493   0.06781  -0.0533   0.0479   1.0000
  14.250   1.4936   0.07916   0.07230  -0.0531   0.0470   1.0000
  14.500   1.4837   0.08364   0.07704  -0.0532   0.0462   1.0000
  14.750   1.4717   0.08854   0.08219  -0.0537   0.0457   1.0000
  15.000   1.4551   0.09420   0.08813  -0.0549   0.0456   1.0000
  15.250   1.4338   0.10069   0.09492  -0.0569   0.0457   1.0000
  15.500   1.4079   0.10831   0.10283  -0.0602   0.0460   1.0000
  15.750   1.3782   0.11721   0.11204  -0.0649   0.0465   1.0000
  16.000   1.3450   0.12777   0.12287  -0.0714   0.0474   1.0000
  16.250   1.3106   0.13988   0.13521  -0.0794   0.0487   1.0000
  16.500   1.2796   0.15245   0.14790  -0.0878   0.0500   1.0000
  16.750   1.2557   0.16426   0.15977  -0.0954   0.0509   1.0000
  17.000   1.1865   0.20116   0.19659  -0.1181   0.0619   1.0000
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