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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.56 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe118-il-1000000-n5.txt
Download as CSV file: xf-goe118-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 118 (MVA MK.7) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2826   0.12154   0.11977  -0.0354   0.9071   0.0022
 -10.250  -0.2772   0.11866   0.11676  -0.0361   0.8788   0.0023
 -10.000  -0.2711   0.11570   0.11370  -0.0371   0.8553   0.0024
  -9.750  -0.2646   0.11268   0.11059  -0.0382   0.8344   0.0025
  -9.500  -0.2578   0.10962   0.10745  -0.0395   0.8159   0.0026
  -9.250  -0.2509   0.10653   0.10429  -0.0408   0.7990   0.0027
  -9.000  -0.2437   0.10342   0.10111  -0.0422   0.7841   0.0029
  -8.750  -0.2359   0.10013   0.09778  -0.0438   0.7712   0.0034
  -8.500  -0.2280   0.09676   0.09436  -0.0457   0.7599   0.0035
  -8.250  -0.2206   0.09343   0.09100  -0.0477   0.7498   0.0036
  -8.000  -0.2131   0.09014   0.08768  -0.0496   0.7409   0.0036
  -7.750  -0.2052   0.08689   0.08441  -0.0516   0.7323   0.0036
  -7.500  -0.1970   0.08362   0.08113  -0.0537   0.7242   0.0036
  -7.250  -0.1886   0.08039   0.07786  -0.0561   0.7169   0.0036
  -7.000  -0.1771   0.07695   0.07440  -0.0595   0.7100   0.0037
  -6.500  -0.1474   0.06815   0.06557  -0.0700   0.6980   0.0038
  -5.000   0.0106   0.04143   0.03843  -0.1066   0.6636   0.0034
  -4.750   0.0450   0.03590   0.03274  -0.1130   0.6585   0.0031
  -4.500   0.0817   0.02906   0.02563  -0.1189   0.6532   0.0029
  -4.250   0.1192   0.01865   0.01446  -0.1237   0.6490   0.0025
  -4.000   0.1502   0.01420   0.00927  -0.1247   0.6440   0.0024
  -3.750   0.1795   0.01203   0.00664  -0.1250   0.6379   0.0025
  -3.500   0.2081   0.01086   0.00517  -0.1252   0.6321   0.0028
  -3.250   0.2367   0.01007   0.00419  -0.1254   0.6257   0.0032
  -3.000   0.2650   0.00960   0.00355  -0.1255   0.6193   0.0036
  -2.750   0.2934   0.00912   0.00297  -0.1258   0.6124   0.0042
  -2.500   0.3215   0.00892   0.00269  -0.1260   0.6040   0.0049
  -2.250   0.3499   0.00859   0.00223  -0.1261   0.5939   0.0055
  -2.000   0.3781   0.00841   0.00195  -0.1263   0.5844   0.0063
  -1.750   0.4063   0.00819   0.00162  -0.1265   0.5766   0.0089
  -1.500   0.4347   0.00810   0.00147  -0.1267   0.5704   0.0110
  -1.250   0.4629   0.00798   0.00127  -0.1268   0.5640   0.0193
  -1.000   0.4911   0.00778   0.00119  -0.1271   0.5570   0.0745
  -0.750   0.5189   0.00783   0.00116  -0.1272   0.5456   0.0819
  -0.250   0.5747   0.00790   0.00115  -0.1276   0.5256   0.0917
   0.000   0.6025   0.00794   0.00112  -0.1277   0.5169   0.0923
   0.250   0.6303   0.00797   0.00111  -0.1279   0.5080   0.0946
   0.500   0.6583   0.00799   0.00112  -0.1280   0.5010   0.0980
   0.750   0.6859   0.00804   0.00115  -0.1282   0.4919   0.1017
   1.000   0.7137   0.00809   0.00117  -0.1283   0.4825   0.1058
   1.250   0.7413   0.00815   0.00122  -0.1285   0.4734   0.1127
   1.750   0.7963   0.00828   0.00135  -0.1288   0.4520   0.1361
   2.250   0.8501   0.00821   0.00165  -0.1292   0.4152   0.3781
   2.750   0.8982   0.00745   0.00207  -0.1284   0.3750   1.0000
   3.000   0.9242   0.00774   0.00225  -0.1283   0.3511   1.0000
   3.250   0.9459   0.00852   0.00265  -0.1276   0.2825   1.0000
   3.500   0.9609   0.01010   0.00355  -0.1259   0.1355   1.0000
   3.750   0.9831   0.01079   0.00401  -0.1253   0.0688   1.0000
   4.000   1.0065   0.01133   0.00441  -0.1247   0.0197   1.0000
   4.250   1.0317   0.01165   0.00470  -0.1245   0.0095   1.0000
   4.500   1.0570   0.01195   0.00505  -0.1242   0.0069   1.0000
   4.750   1.0813   0.01234   0.00545  -0.1237   0.0050   1.0000
   5.000   1.1058   0.01268   0.00582  -0.1234   0.0040   1.0000
   5.250   1.1295   0.01310   0.00627  -0.1229   0.0034   1.0000
   5.500   1.1513   0.01372   0.00699  -0.1220   0.0029   1.0000
   5.750   1.1726   0.01436   0.00772  -0.1210   0.0026   1.0000
   6.000   1.1929   0.01504   0.00849  -0.1198   0.0024   1.0000
   6.250   1.2149   0.01550   0.00898  -0.1191   0.0020   1.0000
   6.500   1.2347   0.01613   0.00966  -0.1181   0.0018   1.0000
   6.750   1.2471   0.01733   0.01099  -0.1157   0.0016   1.0000
   7.000   1.2609   0.01831   0.01208  -0.1135   0.0015   1.0000
   7.250   1.2704   0.01953   0.01342  -0.1107   0.0014   1.0000
   7.500   1.2720   0.02100   0.01503  -0.1064   0.0013   1.0000
   7.750   1.2718   0.02286   0.01704  -0.1020   0.0011   1.0000
   8.000   1.2802   0.02592   0.02020  -0.0983   0.0010   1.0000
   8.250   1.3391   0.03154   0.02598  -0.1015   0.0011   1.0000
   8.500   1.3661   0.03528   0.02995  -0.1006   0.0011   1.0000
   8.750   1.3852   0.03863   0.03354  -0.0988   0.0012   1.0000
   9.000   1.3989   0.04186   0.03700  -0.0965   0.0013   1.0000
   9.250   1.4079   0.04501   0.04039  -0.0938   0.0014   1.0000
   9.500   1.4119   0.04817   0.04376  -0.0909   0.0015   1.0000
   9.750   1.4002   0.05251   0.04835  -0.0871   0.0016   1.0000
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