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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 100,000
Max Cl/Cd: 62 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe118-il-100000.txt
Download as CSV file: xf-goe118-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3064   0.10166   0.09765  -0.0320   1.0000   0.0688
  -7.250  -0.3324   0.10231   0.09845  -0.0265   1.0000   0.0688
  -7.000  -0.3563   0.10278   0.09904  -0.0221   1.0000   0.0688
  -6.750  -0.3159   0.09915   0.09539  -0.0458   0.9860   0.0705
  -6.500  -0.3040   0.09244   0.08868  -0.0372   0.9851   0.0731
  -6.250  -0.2767   0.08799   0.08420  -0.0427   0.9774   0.0776
  -6.000  -0.2206   0.08429   0.08033  -0.0703   0.9625   0.0836
  -5.750  -0.2112   0.07823   0.07435  -0.0633   0.9594   0.0859
  -5.500  -0.1819   0.07399   0.07006  -0.0678   0.9525   0.0916
  -5.250  -0.1357   0.06861   0.06455  -0.0827   0.9438   0.0988
  -5.000  -0.1125   0.06497   0.06089  -0.0838   0.9359   0.1058
  -4.750  -0.0618   0.05934   0.05507  -0.0967   0.9301   0.1132
  -4.500  -0.0332   0.05555   0.05117  -0.0999   0.9213   0.1171
  -4.250   0.0230   0.05024   0.04548  -0.1122   0.9160   0.1260
  -4.000   0.0497   0.04665   0.04183  -0.1141   0.9067   0.1284
  -3.750   0.1182   0.03623   0.03026  -0.1260   0.9027   0.0695
  -3.500   0.1544   0.03032   0.02347  -0.1288   0.8942   0.0582
  -3.250   0.1943   0.02651   0.01915  -0.1316   0.8893   0.0565
  -3.000   0.2261   0.02410   0.01610  -0.1322   0.8804   0.0586
  -2.750   0.2630   0.02263   0.01442  -0.1335   0.8749   0.0651
  -2.500   0.2915   0.02121   0.01262  -0.1331   0.8653   0.0701
  -2.250   0.3230   0.02024   0.01155  -0.1332   0.8579   0.0845
  -2.000   0.3528   0.01986   0.01118  -0.1332   0.8495   0.1431
  -1.750   0.3792   0.01985   0.01102  -0.1330   0.8402   0.1828
  -1.500   0.4092   0.01964   0.01073  -0.1333   0.8338   0.2131
  -1.250   0.4340   0.01966   0.01062  -0.1329   0.8236   0.2349
  -1.000   0.4608   0.01937   0.01031  -0.1326   0.8152   0.2405
  -0.750   0.4890   0.01907   0.00990  -0.1322   0.8078   0.2483
  -0.500   0.5139   0.01894   0.00979  -0.1316   0.7984   0.2598
  -0.250   0.5424   0.01861   0.00950  -0.1313   0.7913   0.2831
   0.000   0.5668   0.01677   0.00944  -0.1304   0.7826   1.0000
   0.250   0.5938   0.01700   0.00927  -0.1298   0.7739   1.0000
   0.500   0.6219   0.01708   0.00909  -0.1294   0.7666   1.0000
   0.750   0.6468   0.01740   0.00927  -0.1289   0.7569   1.0000
   1.000   0.6738   0.01758   0.00930  -0.1286   0.7493   1.0000
   1.250   0.7001   0.01780   0.00942  -0.1282   0.7409   1.0000
   1.500   0.7253   0.01814   0.00969  -0.1278   0.7322   1.0000
   1.750   0.7533   0.01825   0.00969  -0.1275   0.7255   1.0000
   2.000   0.7775   0.01867   0.01010  -0.1271   0.7160   1.0000
   2.250   0.8045   0.01889   0.01031  -0.1268   0.7091   1.0000
   2.500   0.8299   0.01923   0.01065  -0.1265   0.7005   1.0000
   2.750   0.8550   0.01961   0.01106  -0.1261   0.6923   1.0000
   3.000   0.8823   0.01981   0.01125  -0.1258   0.6853   1.0000
   3.250   0.9062   0.02030   0.01182  -0.1254   0.6762   1.0000
   3.500   0.9349   0.02041   0.01199  -0.1252   0.6702   1.0000
   3.750   0.9576   0.02099   0.01272  -0.1247   0.6606   1.0000
   4.000   0.9829   0.02121   0.01304  -0.1241   0.6511   1.0000
   4.250   1.0099   0.01953   0.01120  -0.1213   0.6237   1.0000
   4.500   1.0359   0.01863   0.01022  -0.1194   0.6011   1.0000
   4.750   1.0570   0.01791   0.00959  -0.1169   0.5688   1.0000
   5.000   1.0762   0.01746   0.00910  -0.1142   0.5269   1.0000
   5.250   1.0894   0.01757   0.00889  -0.1108   0.4459   1.0000
   5.500   1.0901   0.01944   0.00961  -0.1064   0.2745   1.0000
   5.750   1.0810   0.02306   0.01195  -0.1017   0.0666   1.0000
   6.000   1.0958   0.02432   0.01333  -0.0995   0.0561   1.0000
   6.250   1.1099   0.02553   0.01475  -0.0973   0.0519   1.0000
   6.500   1.1179   0.02712   0.01653  -0.0945   0.0489   1.0000
   6.750   1.1244   0.02864   0.01826  -0.0915   0.0460   1.0000
   7.000   1.1263   0.03021   0.01999  -0.0880   0.0441   1.0000
   7.250   1.1266   0.03200   0.02199  -0.0846   0.0437   1.0000
   7.500   1.1281   0.03389   0.02396  -0.0814   0.0436   1.0000
   7.750   1.1355   0.03568   0.02576  -0.0786   0.0438   1.0000
   8.000   1.1642   0.03729   0.02725  -0.0769   0.0450   1.0000
   8.250   1.2528   0.04063   0.03038  -0.0823   0.0496   1.0000
   8.500   1.2911   0.04299   0.03312  -0.0820   0.0522   1.0000
   8.750   1.3415   0.04655   0.03704  -0.0828   0.0623   1.0000
  10.500   1.3102   0.08235   0.07847  -0.0639   0.2389   1.0000
  10.750   1.2748   0.08677   0.08291  -0.0631   0.2273   1.0000
  11.000   1.2403   0.09258   0.08873  -0.0640   0.2168   1.0000
  11.250   1.2074   0.10070   0.09686  -0.0670   0.2136   1.0000
  11.500   1.1731   0.10841   0.10453  -0.0703   0.2020   1.0000
  11.750   1.0749   0.09519   0.09140  -0.0438   0.1757   1.0000
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