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GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 701 AIRFOIL (goe701-il)
Reynolds number: 200,000
Max Cl/Cd: 78.87 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe701-il-200000.txt
Download as CSV file: xf-goe701-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 701 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  -0.2654   0.09145   0.08797  -0.0547   0.9810   0.0923
  -8.250  -0.2899   0.08519   0.08171  -0.0728   0.9638   0.0980
  -8.000  -0.2791   0.07802   0.07451  -0.0794   0.9577   0.0990
  -7.750  -0.2491   0.07682   0.07332  -0.0753   0.9572   0.1004
  -7.500  -0.2198   0.07424   0.07071  -0.0772   0.9553   0.1025
  -7.250  -0.2738   0.05189   0.04782  -0.0980   0.9312   0.0871
  -7.000  -0.2559   0.04603   0.04171  -0.1015   0.9265   0.0850
  -6.750  -0.2546   0.03957   0.03484  -0.1021   0.9176   0.0842
  -6.500  -0.2482   0.03241   0.02682  -0.1028   0.9110   0.0853
  -6.250  -0.2212   0.02859   0.02242  -0.1045   0.9086   0.0872
  -6.000  -0.2067   0.02762   0.02138  -0.1023   0.8997   0.0885
  -5.750  -0.1720   0.02667   0.02039  -0.1039   0.8965   0.0907
  -5.500  -0.1354   0.02537   0.01887  -0.1058   0.8943   0.0938
  -5.250  -0.0997   0.02369   0.01676  -0.1075   0.8923   0.0970
  -5.000  -0.0859   0.02274   0.01553  -0.1048   0.8829   0.0989
  -4.750  -0.0513   0.02165   0.01445  -0.1062   0.8797   0.1020
  -4.500  -0.0136   0.02096   0.01369  -0.1080   0.8773   0.1062
  -4.250   0.0107   0.02039   0.01291  -0.1071   0.8708   0.1100
  -4.000   0.0390   0.01941   0.01179  -0.1071   0.8653   0.1139
  -3.750   0.0753   0.01884   0.01124  -0.1086   0.8621   0.1193
  -3.500   0.1134   0.01830   0.01050  -0.1102   0.8594   0.1260
  -3.250   0.1306   0.01780   0.01006  -0.1081   0.8501   0.1309
  -3.000   0.1651   0.01738   0.00957  -0.1091   0.8460   0.1386
  -2.750   0.1993   0.01683   0.00900  -0.1101   0.8420   0.1463
  -2.500   0.2204   0.01675   0.00890  -0.1086   0.8334   0.1530
  -2.250   0.2543   0.01628   0.00836  -0.1095   0.8288   0.1605
  -2.000   0.2807   0.01613   0.00824  -0.1090   0.8221   0.1674
  -1.750   0.3082   0.01597   0.00798  -0.1087   0.8152   0.1744
  -1.500   0.3427   0.01554   0.00760  -0.1097   0.8107   0.1821
  -1.250   0.3640   0.01554   0.00755  -0.1083   0.8020   0.1891
  -1.000   0.3947   0.01518   0.00724  -0.1086   0.7961   0.1975
  -0.750   0.4213   0.01510   0.00712  -0.1081   0.7891   0.2063
  -0.500   0.4472   0.01481   0.00690  -0.1075   0.7815   0.2144
  -0.250   0.4790   0.01454   0.00660  -0.1080   0.7756   0.2260
   0.000   0.5002   0.01436   0.00651  -0.1064   0.7656   0.2383
   0.250   0.5294   0.01402   0.00621  -0.1064   0.7578   0.2565
   0.500   0.5519   0.01372   0.00603  -0.1050   0.7472   0.2799
   0.750   0.5751   0.01340   0.00589  -0.1038   0.7371   0.3192
   1.000   0.5968   0.01271   0.00572  -0.1023   0.7279   0.4629
   1.250   0.7366   0.01162   0.00571  -0.1250   0.7171   1.0000
   1.500   0.7631   0.01166   0.00561  -0.1245   0.7095   1.0000
   1.750   0.7818   0.01177   0.00569  -0.1225   0.6991   1.0000
   2.000   0.8057   0.01184   0.00566  -0.1215   0.6903   1.0000
   2.250   0.8267   0.01191   0.00568  -0.1199   0.6799   1.0000
   2.500   0.8478   0.01201   0.00573  -0.1183   0.6696   1.0000
   2.750   0.8721   0.01207   0.00569  -0.1173   0.6602   1.0000
   3.000   0.8906   0.01219   0.00581  -0.1153   0.6488   1.0000
   3.250   0.9122   0.01229   0.00586  -0.1138   0.6384   1.0000
   3.500   0.9345   0.01238   0.00588  -0.1125   0.6274   1.0000
   3.750   0.9527   0.01250   0.00598  -0.1104   0.6145   1.0000
   4.000   0.9721   0.01263   0.00608  -0.1085   0.6017   1.0000
   4.250   0.9920   0.01277   0.00616  -0.1067   0.5888   1.0000
   4.500   1.0117   0.01292   0.00625  -0.1049   0.5756   1.0000
   4.750   1.0304   0.01309   0.00635  -0.1029   0.5612   1.0000
   5.000   1.0474   0.01328   0.00650  -0.1005   0.5453   1.0000
   5.250   1.0638   0.01350   0.00666  -0.0981   0.5285   1.0000
   5.500   1.0787   0.01374   0.00684  -0.0954   0.5102   1.0000
   5.750   1.0927   0.01401   0.00706  -0.0926   0.4910   1.0000
   6.000   1.1051   0.01432   0.00729  -0.0895   0.4699   1.0000
   6.250   1.1158   0.01469   0.00754  -0.0861   0.4477   1.0000
   6.500   1.1252   0.01510   0.00785  -0.0825   0.4243   1.0000
   6.750   1.1323   0.01557   0.00820  -0.0785   0.4017   1.0000
   7.000   1.1387   0.01609   0.00857  -0.0745   0.3818   1.0000
   7.250   1.1465   0.01663   0.00900  -0.0708   0.3627   1.0000
   7.500   1.1561   0.01720   0.00947  -0.0676   0.3464   1.0000
   8.000   1.1795   0.01835   0.01048  -0.0622   0.3198   1.0000
   8.250   1.1933   0.01893   0.01103  -0.0600   0.3090   1.0000
   8.500   1.2073   0.01958   0.01157  -0.0579   0.2998   1.0000
   8.750   1.2214   0.02011   0.01214  -0.0558   0.2903   1.0000
   9.000   1.2357   0.02076   0.01273  -0.0538   0.2818   1.0000
   9.250   1.2494   0.02134   0.01334  -0.0518   0.2735   1.0000
   9.500   1.2638   0.02201   0.01397  -0.0500   0.2658   1.0000
   9.750   1.2775   0.02260   0.01463  -0.0481   0.2585   1.0000
  10.000   1.2930   0.02333   0.01528  -0.0465   0.2517   1.0000
  10.250   1.3051   0.02395   0.01602  -0.0445   0.2448   1.0000
  10.500   1.3190   0.02469   0.01671  -0.0428   0.2385   1.0000
  10.750   1.3313   0.02541   0.01752  -0.0409   0.2319   1.0000
  11.000   1.3415   0.02617   0.01832  -0.0389   0.2251   1.0000
  11.250   1.3536   0.02700   0.01917  -0.0372   0.2189   1.0000
  11.500   1.3642   0.02781   0.02009  -0.0353   0.2129   1.0000
  11.750   1.3744   0.02872   0.02098  -0.0336   0.2069   1.0000
  12.000   1.3840   0.02964   0.02203  -0.0318   0.2010   1.0000
  12.250   1.3928   0.03061   0.02309  -0.0301   0.1951   1.0000
  12.500   1.4003   0.03173   0.02422  -0.0284   0.1889   1.0000
  12.750   1.4079   0.03283   0.02549  -0.0268   0.1823   1.0000
  13.000   1.4135   0.03413   0.02680  -0.0252   0.1762   1.0000
  13.250   1.4215   0.03534   0.02818  -0.0238   0.1692   1.0000
  13.500   1.4258   0.03685   0.02973  -0.0224   0.1623   1.0000
  13.750   1.4317   0.03835   0.03136  -0.0213   0.1525   1.0000
  14.000   1.4349   0.04015   0.03321  -0.0201   0.1412   1.0000
  14.250   1.4350   0.04232   0.03539  -0.0190   0.1265   1.0000
  14.500   1.4315   0.04496   0.03798  -0.0179   0.1104   1.0000
  14.750   1.4232   0.04819   0.04113  -0.0169   0.0910   1.0000
  15.000   1.4116   0.05191   0.04476  -0.0160   0.0737   1.0000
  15.250   1.4003   0.05579   0.04858  -0.0154   0.0595   1.0000
  15.500   1.3895   0.05977   0.05256  -0.0151   0.0527   1.0000
  15.750   1.3792   0.06388   0.05670  -0.0151   0.0491   1.0000
  16.000   1.3689   0.06816   0.06107  -0.0153   0.0465   1.0000
  16.250   1.3582   0.07264   0.06565  -0.0159   0.0449   1.0000
  16.500   1.3452   0.07757   0.07068  -0.0167   0.0436   1.0000
  16.750   1.3310   0.08286   0.07607  -0.0178   0.0426   1.0000
  17.000   1.3210   0.08765   0.08099  -0.0189   0.0417   1.0000
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