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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 50,000
Max Cl/Cd: 43.42 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610bm-il-50000-n5.txt
Download as CSV file: xf-goe610bm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2898   0.10349   0.09730  -0.0287   1.0000   0.0748
  -7.000  -0.2968   0.10281   0.09677  -0.0296   1.0000   0.0766
  -6.750  -0.3021   0.10229   0.09638  -0.0320   1.0000   0.0774
  -6.500  -0.3035   0.10141   0.09559  -0.0352   1.0000   0.0778
  -6.250  -0.3021   0.09601   0.09029  -0.0292   1.0000   0.0795
  -6.000  -0.3015   0.09310   0.08740  -0.0265   1.0000   0.0820
  -5.750  -0.3020   0.09094   0.08532  -0.0256   1.0000   0.0847
  -5.500  -0.3014   0.08894   0.08338  -0.0261   1.0000   0.0880
  -5.250  -0.2896   0.08799   0.08241  -0.0351   1.0000   0.0925
  -5.000  -0.2735   0.08273   0.07720  -0.0353   0.9952   0.0950
  -4.500  -0.2080   0.07385   0.06819  -0.0475   0.9792   0.1164
  -4.250  -0.1510   0.06987   0.06394  -0.0637   0.9703   0.1371
  -3.750  -0.0952   0.06124   0.05524  -0.0688   0.9552   0.1579
  -3.500  -0.0034   0.05300   0.04608  -0.0896   0.9495   0.0926
  -3.250   0.0391   0.04766   0.04048  -0.0949   0.9422   0.0761
  -3.000   0.0881   0.04323   0.03570  -0.1014   0.9369   0.0726
  -2.750   0.1368   0.03958   0.03141  -0.1074   0.9286   0.0761
  -2.500   0.1868   0.03607   0.02734  -0.1129   0.9233   0.0750
  -2.250   0.2285   0.03345   0.02415  -0.1161   0.9143   0.0746
  -2.000   0.2710   0.03135   0.02143  -0.1192   0.9061   0.0793
  -1.750   0.3102   0.02964   0.01942  -0.1216   0.8977   0.0821
  -1.500   0.3457   0.02826   0.01758  -0.1228   0.8871   0.0821
  -1.250   0.3820   0.02708   0.01604  -0.1241   0.8774   0.0828
  -1.000   0.4175   0.02609   0.01473  -0.1249   0.8678   0.0840
  -0.750   0.4489   0.02539   0.01374  -0.1251   0.8556   0.0858
  -0.500   0.4799   0.02480   0.01292  -0.1252   0.8434   0.0885
  -0.250   0.5107   0.02431   0.01221  -0.1252   0.8312   0.0923
   0.000   0.5416   0.02380   0.01164  -0.1254   0.8191   0.1011
   0.250   0.5726   0.02334   0.01116  -0.1256   0.8072   0.1222
   0.500   0.6034   0.02276   0.01087  -0.1259   0.7951   0.1764
   0.750   0.6245   0.02085   0.01060  -0.1241   0.7818   1.0000
   1.000   0.6525   0.02100   0.01038  -0.1236   0.7685   1.0000
   1.250   0.6803   0.02117   0.01028  -0.1232   0.7554   1.0000
   1.500   0.7081   0.02136   0.01025  -0.1228   0.7427   1.0000
   1.750   0.7358   0.02157   0.01027  -0.1225   0.7302   1.0000
   2.000   0.7637   0.02178   0.01032  -0.1222   0.7186   1.0000
   2.250   0.7913   0.02202   0.01043  -0.1218   0.7071   1.0000
   2.500   0.8174   0.02238   0.01070  -0.1215   0.6943   1.0000
   2.750   0.8436   0.02275   0.01101  -0.1212   0.6824   1.0000
   3.000   0.8702   0.02310   0.01130  -0.1209   0.6715   1.0000
   3.250   0.8976   0.02337   0.01155  -0.1205   0.6618   1.0000
   3.500   0.9228   0.02386   0.01205  -0.1202   0.6502   1.0000
   3.750   0.9485   0.02430   0.01252  -0.1199   0.6400   1.0000
   4.000   0.9758   0.02460   0.01285  -0.1196   0.6314   1.0000
   4.250   1.0005   0.02515   0.01348  -0.1193   0.6210   1.0000
   4.500   1.0259   0.02563   0.01404  -0.1189   0.6116   1.0000
   4.750   1.0528   0.02598   0.01449  -0.1186   0.6035   1.0000
   5.000   1.0769   0.02661   0.01526  -0.1182   0.5938   1.0000
   5.250   1.1032   0.02702   0.01577  -0.1178   0.5857   1.0000
   5.500   1.1280   0.02759   0.01649  -0.1174   0.5766   1.0000
   5.750   1.1522   0.02809   0.01719  -0.1167   0.5659   1.0000
   6.000   1.1766   0.02836   0.01757  -0.1157   0.5524   1.0000
   6.250   1.2001   0.02852   0.01782  -0.1144   0.5357   1.0000
   6.500   1.2233   0.02870   0.01810  -0.1131   0.5183   1.0000
   6.750   1.2461   0.02905   0.01865  -0.1119   0.5025   1.0000
   7.000   1.2681   0.02943   0.01919  -0.1106   0.4862   1.0000
   7.250   1.2841   0.02961   0.01945  -0.1081   0.4571   1.0000
   7.500   1.2979   0.02989   0.01979  -0.1055   0.4251   1.0000
   7.750   1.3114   0.03044   0.02048  -0.1032   0.3952   1.0000
   8.000   1.3251   0.03116   0.02138  -0.1011   0.3669   1.0000
   8.250   1.3364   0.03202   0.02243  -0.0987   0.3313   1.0000
   8.500   1.3452   0.03310   0.02346  -0.0961   0.2861   1.0000
   8.750   1.3472   0.03474   0.02474  -0.0929   0.2311   1.0000
   9.000   1.3485   0.03667   0.02648  -0.0900   0.1957   1.0000
   9.250   1.3466   0.03878   0.02850  -0.0869   0.1700   1.0000
   9.500   1.3425   0.04133   0.03096  -0.0841   0.1436   1.0000
   9.750   1.3391   0.04406   0.03368  -0.0819   0.1180   1.0000
  10.000   1.3338   0.04717   0.03674  -0.0800   0.0845   1.0000
  10.250   1.3228   0.05108   0.04041  -0.0785   0.0533   1.0000
  10.500   1.3143   0.05495   0.04422  -0.0775   0.0432   1.0000
  10.750   1.3078   0.05879   0.04812  -0.0767   0.0388   1.0000
  11.000   1.3011   0.06280   0.05221  -0.0762   0.0361   1.0000
  11.250   1.2956   0.06678   0.05636  -0.0759   0.0340   1.0000
  11.500   1.2895   0.07095   0.06069  -0.0759   0.0322   1.0000
  11.750   1.2825   0.07533   0.06523  -0.0760   0.0308   1.0000
  12.000   1.2747   0.07994   0.06996  -0.0764   0.0298   1.0000
  12.250   1.2695   0.08425   0.07445  -0.0767   0.0289   1.0000
  12.500   1.2645   0.08857   0.07906  -0.0771   0.0283   1.0000
  12.750   1.2600   0.09286   0.08356  -0.0775   0.0278   1.0000
  13.000   1.2563   0.09709   0.08799  -0.0780   0.0273   1.0000
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