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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 100,000
Max Cl/Cd: 61.72 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe118-il-100000-n5.txt
Download as CSV file: xf-goe118-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2715   0.11660   0.11206  -0.0426   1.0000   0.0305
  -9.000  -0.2722   0.11462   0.11017  -0.0435   1.0000   0.0306
  -8.750  -0.2743   0.11269   0.10834  -0.0437   1.0000   0.0307
  -8.500  -0.2620   0.10697   0.10265  -0.0415   1.0000   0.0316
  -8.250  -0.2613   0.10452   0.10027  -0.0400   1.0000   0.0325
  -8.000  -0.2601   0.10226   0.09808  -0.0397   0.9977   0.0334
  -7.750  -0.2416   0.09828   0.09406  -0.0445   0.9883   0.0351
  -7.500  -0.2236   0.09448   0.09027  -0.0503   0.9766   0.0375
  -7.250  -0.2048   0.09154   0.08736  -0.0619   0.9568   0.0394
  -7.000  -0.1898   0.08656   0.08239  -0.0623   0.9476   0.0411
  -6.750  -0.1704   0.08299   0.07878  -0.0646   0.9375   0.0453
  -6.500  -0.1366   0.08002   0.07575  -0.0820   0.9189   0.0503
  -6.250  -0.1283   0.07510   0.07085  -0.0783   0.9108   0.0526
  -6.000  -0.1093   0.07176   0.06746  -0.0800   0.9008   0.0567
  -5.750  -0.0616   0.06859   0.06403  -0.0999   0.8845   0.0643
  -5.500  -0.0554   0.06370   0.05923  -0.0965   0.8750   0.0657
  -5.250  -0.0387   0.06030   0.05577  -0.0969   0.8644   0.0674
  -5.000  -0.0017   0.05202   0.04722  -0.1059   0.8548   0.0292
  -4.750   0.0263   0.04767   0.04271  -0.1102   0.8461   0.0257
  -4.250   0.1003   0.03566   0.02992  -0.1215   0.8281   0.0200
  -4.000   0.1325   0.03106   0.02479  -0.1248   0.8201   0.0195
  -3.750   0.1643   0.02716   0.02024  -0.1270   0.8116   0.0192
  -3.500   0.1964   0.02429   0.01663  -0.1282   0.8045   0.0197
  -3.250   0.2259   0.02209   0.01381  -0.1287   0.7956   0.0213
  -3.000   0.2551   0.02023   0.01153  -0.1290   0.7886   0.0228
  -2.750   0.2835   0.01899   0.00999  -0.1290   0.7801   0.0241
  -2.500   0.3120   0.01802   0.00871  -0.1289   0.7727   0.0266
  -2.250   0.3402   0.01720   0.00764  -0.1288   0.7649   0.0325
  -2.000   0.3684   0.01652   0.00678  -0.1287   0.7575   0.0401
  -1.750   0.3965   0.01640   0.00683  -0.1286   0.7499   0.1116
  -1.500   0.4240   0.01666   0.00686  -0.1286   0.7422   0.1459
  -1.250   0.4515   0.01662   0.00662  -0.1286   0.7351   0.1631
  -1.000   0.4782   0.01644   0.00632  -0.1284   0.7273   0.1665
  -0.750   0.5054   0.01629   0.00600  -0.1282   0.7205   0.1708
  -0.500   0.5321   0.01621   0.00581  -0.1281   0.7127   0.1767
  -0.250   0.5598   0.01610   0.00560  -0.1280   0.7060   0.1855
   0.000   0.5869   0.01602   0.00551  -0.1281   0.6982   0.2017
   0.250   0.6145   0.01580   0.00540  -0.1281   0.6915   0.2587
   0.750   0.6653   0.01441   0.00535  -0.1271   0.6769   1.0000
   1.000   0.6916   0.01459   0.00541  -0.1269   0.6684   1.0000
   1.250   0.7189   0.01474   0.00539  -0.1268   0.6618   1.0000
   1.500   0.7450   0.01493   0.00553  -0.1266   0.6533   1.0000
   1.750   0.7720   0.01509   0.00561  -0.1265   0.6467   1.0000
   2.000   0.7981   0.01530   0.00580  -0.1263   0.6388   1.0000
   2.250   0.8250   0.01547   0.00592  -0.1262   0.6324   1.0000
   2.500   0.8510   0.01569   0.00616  -0.1260   0.6246   1.0000
   2.750   0.8778   0.01588   0.00637  -0.1259   0.6184   1.0000
   3.000   0.9036   0.01612   0.00668  -0.1257   0.6107   1.0000
   3.250   0.9303   0.01632   0.00690  -0.1256   0.6047   1.0000
   3.500   0.9559   0.01659   0.00734  -0.1254   0.5968   1.0000
   3.750   0.9826   0.01680   0.00761  -0.1252   0.5909   1.0000
   4.000   1.0078   0.01710   0.00810  -0.1249   0.5827   1.0000
   4.250   1.0320   0.01719   0.00828  -0.1241   0.5675   1.0000
   4.500   1.0505   0.01702   0.00803  -0.1217   0.5226   1.0000
   4.750   1.0643   0.01736   0.00803  -0.1188   0.4432   1.0000
   5.000   1.0604   0.01974   0.00898  -0.1141   0.2317   1.0000
   5.250   1.0541   0.02310   0.01122  -0.1097   0.0350   1.0000
   5.500   1.0693   0.02428   0.01259  -0.1077   0.0268   1.0000
   5.750   1.0810   0.02566   0.01425  -0.1053   0.0236   1.0000
   6.000   1.0940   0.02684   0.01568  -0.1031   0.0219   1.0000
   6.250   1.1033   0.02817   0.01725  -0.1006   0.0194   1.0000
   6.500   1.1060   0.02972   0.01904  -0.0972   0.0176   1.0000
   6.750   1.1048   0.03158   0.02107  -0.0937   0.0170   1.0000
   7.000   1.1010   0.03375   0.02337  -0.0904   0.0165   1.0000
   7.250   1.0977   0.03607   0.02576  -0.0873   0.0161   1.0000
   7.500   1.1007   0.03832   0.02791  -0.0843   0.0158   1.0000
   7.750   1.1180   0.03979   0.02942  -0.0823   0.0154   1.0000
   8.000   1.1374   0.04108   0.03087  -0.0807   0.0144   1.0000
   8.250   1.1645   0.04255   0.03247  -0.0795   0.0133   1.0000
   8.500   1.2112   0.04483   0.03486  -0.0799   0.0132   1.0000
   8.750   1.2584   0.04818   0.03855  -0.0814   0.0135   1.0000
   9.000   1.2914   0.05190   0.04256  -0.0816   0.0140   1.0000
   9.250   1.3155   0.05605   0.04699  -0.0811   0.0147   1.0000
   9.500   1.3368   0.05880   0.05009  -0.0795   0.0172   1.0000
   9.750   1.3454   0.06183   0.05368  -0.0759   0.0203   1.0000
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