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GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il)
Reynolds number: 50,000
Max Cl/Cd: 24.28 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe118-il-50000.txt
Download as CSV file: xf-goe118-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2807   0.11170   0.10541  -0.0362   1.0000   0.1322
  -8.250  -0.2840   0.11027   0.10411  -0.0365   1.0000   0.1359
  -8.000  -0.2978   0.11051   0.10454  -0.0362   1.0000   0.1375
  -7.750  -0.3173   0.11120   0.10545  -0.0346   1.0000   0.1380
  -7.500  -0.2967   0.10432   0.09856  -0.0330   1.0000   0.1419
  -7.250  -0.3046   0.10281   0.09718  -0.0302   1.0000   0.1445
  -7.000  -0.3204   0.10230   0.09683  -0.0269   1.0000   0.1464
  -6.750  -0.3374   0.10201   0.09668  -0.0242   1.0000   0.1483
  -6.500  -0.3556   0.10205   0.09686  -0.0225   1.0000   0.1501
  -6.250  -0.3730   0.10251   0.09745  -0.0231   1.0000   0.1514
  -6.000  -0.3793   0.10032   0.09535  -0.0222   1.0000   0.1527
  -5.750  -0.3794   0.09693   0.09201  -0.0184   1.0000   0.1556
  -5.500  -0.3827   0.09494   0.09007  -0.0174   1.0000   0.1592
  -5.250  -0.3852   0.09382   0.08899  -0.0208   1.0000   0.1643
  -5.000  -0.3838   0.09114   0.08636  -0.0222   1.0000   0.1669
  -4.750  -0.3822   0.08815   0.08340  -0.0198   1.0000   0.1708
  -4.500  -0.3690   0.08645   0.08165  -0.0280   1.0000   0.1795
  -4.250  -0.3680   0.08278   0.07805  -0.0240   1.0000   0.1829
  -4.000  -0.3506   0.08025   0.07544  -0.0302   1.0000   0.1938
  -3.750  -0.3382   0.07668   0.07189  -0.0294   0.9980   0.2019
  -3.500  -0.2942   0.07225   0.06731  -0.0394   0.9899   0.2227
  -3.250  -0.2523   0.06819   0.06313  -0.0468   0.9824   0.2499
  -3.000  -0.2220   0.06509   0.05989  -0.0508   0.9742   0.2904
  -2.750  -0.2016   0.06176   0.05663  -0.0495   0.9673   0.3367
  -2.250   0.0101   0.04700   0.03964  -0.0943   0.9528   0.1318
  -2.000   0.0698   0.04280   0.03454  -0.1013   0.9459   0.1176
  -1.750   0.1235   0.04012   0.03098  -0.1065   0.9389   0.1227
  -1.500   0.1699   0.03823   0.02856  -0.1105   0.9313   0.1410
  -1.250   0.2139   0.03632   0.02621  -0.1135   0.9238   0.1741
  -1.000   0.2594   0.03509   0.02502  -0.1172   0.9164   0.2948
  -0.750   0.2879   0.03520   0.02502  -0.1181   0.9067   0.3403
  -0.500   0.3250   0.03526   0.02479  -0.1202   0.8978   0.3549
  -0.250   0.3647   0.03523   0.02463  -0.1227   0.8891   0.3800
   0.000   0.3916   0.03535   0.02488  -0.1234   0.8792   0.4206
   0.250   0.4167   0.03401   0.02490  -0.1227   0.8705   1.0000
   0.500   0.4571   0.03474   0.02485  -0.1249   0.8613   1.0000
   0.750   0.4780   0.03570   0.02549  -0.1245   0.8505   1.0000
   1.000   0.5024   0.03665   0.02615  -0.1247   0.8403   1.0000
   1.250   0.5334   0.03749   0.02675  -0.1259   0.8308   1.0000
   1.500   0.5648   0.03828   0.02737  -0.1270   0.8212   1.0000
   1.750   0.5819   0.03945   0.02843  -0.1263   0.8105   1.0000
   2.000   0.6041   0.04054   0.02943  -0.1262   0.8005   1.0000
   2.250   0.6396   0.04127   0.03007  -0.1277   0.7920   1.0000
   2.500   0.6558   0.04258   0.03133  -0.1270   0.7816   1.0000
   2.750   0.6707   0.04400   0.03273  -0.1262   0.7715   1.0000
   3.000   0.6963   0.04513   0.03384  -0.1265   0.7628   1.0000
   3.250   0.7190   0.04635   0.03507  -0.1266   0.7538   1.0000
   3.500   0.7275   0.04820   0.03699  -0.1253   0.7442   1.0000
   3.750   0.7532   0.04944   0.03827  -0.1257   0.7363   1.0000
   4.000   0.7658   0.05122   0.04010  -0.1250   0.7276   1.0000
   4.250   0.7743   0.05330   0.04223  -0.1240   0.7197   1.0000
   4.500   0.7965   0.05486   0.04387  -0.1242   0.7129   1.0000
   4.750   0.7976   0.05739   0.04646  -0.1228   0.7057   1.0000
   5.000   0.8168   0.05918   0.04836  -0.1229   0.6996   1.0000
   5.250   0.8230   0.06174   0.05109  -0.1222   0.6949   1.0000
   5.500   0.8205   0.06470   0.05413  -0.1210   0.6915   1.0000
   5.750   0.8276   0.06729   0.05683  -0.1206   0.6884   1.0000
   6.000   0.8325   0.07013   0.05979  -0.1203   0.6875   1.0000
   6.250   0.8265   0.07376   0.06351  -0.1198   0.6930   1.0000
   6.500   0.8417   0.07680   0.06672  -0.1208   0.6970   1.0000
   6.750   0.9108   0.07180   0.06215  -0.1172   0.6346   1.0000
   7.000   0.8872   0.07760   0.06798  -0.1174   0.6494   1.0000
   7.250   0.8686   0.08317   0.07361  -0.1183   0.6727   1.0000
   7.500   0.8554   0.08731   0.07784  -0.1180   0.6871   1.0000
   7.750   0.8453   0.09104   0.08168  -0.1177   0.7016   1.0000
   8.000   1.0901   0.04552   0.03394  -0.0770   0.0845   1.0000
   8.250   1.0871   0.04860   0.03716  -0.0754   0.0829   1.0000
   8.500   1.0873   0.05137   0.04012  -0.0737   0.0815   1.0000
   8.750   1.0902   0.05381   0.04271  -0.0717   0.0803   1.0000
   9.000   1.0995   0.05552   0.04453  -0.0691   0.0785   1.0000
   9.250   1.2945   0.05332   0.04230  -0.0704   0.0757   1.0000
   9.500   1.3855   0.05994   0.04927  -0.0753   0.0841   1.0000
   9.750   1.3882   0.06127   0.05153  -0.0709   0.0893   1.0000
  10.000   1.4217   0.06616   0.05686  -0.0703   0.0973   1.0000
  10.250   1.4199   0.06964   0.06109  -0.0665   0.1034   1.0000
  10.500   1.4282   0.07401   0.06595  -0.0642   0.1096   1.0000
  10.750   1.4087   0.07747   0.07000  -0.0601   0.1138   1.0000
  11.000   1.4151   0.08297   0.07583  -0.0586   0.1210   1.0000
  11.250   1.3820   0.08573   0.07898  -0.0544   0.1225   1.0000
  11.500   1.3497   0.08931   0.08282  -0.0515   0.1234   1.0000
  11.750   1.3176   0.09368   0.08743  -0.0503   0.1240   1.0000
  12.000   1.2854   0.09884   0.09277  -0.0505   0.1242   1.0000
  12.250   1.2530   0.10478   0.09886  -0.0520   0.1239   1.0000
  12.500   1.2207   0.11156   0.10575  -0.0548   0.1234   1.0000
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