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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 100,000
Max Cl/Cd: 60.78 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe164-il-100000.txt
Download as CSV file: xf-goe164-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 164 (MVA MK.10) 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
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2999   0.09895   0.09479  -0.0187   1.0000   0.0853
  -6.500  -0.3147   0.09909   0.09508  -0.0203   1.0000   0.0868
  -6.250  -0.3243   0.09929   0.09538  -0.0255   1.0000   0.0874
  -6.000  -0.3225   0.09411   0.09025  -0.0163   1.0000   0.0893
  -5.750  -0.3241   0.09223   0.08843  -0.0131   1.0000   0.0919
  -5.500  -0.3276   0.09074   0.08700  -0.0121   1.0000   0.0946
  -5.250  -0.3010   0.08868   0.08492  -0.0299   0.9966   0.1007
  -5.000  -0.2886   0.08392   0.08019  -0.0247   0.9925   0.1029
  -4.750  -0.2520   0.08001   0.07624  -0.0313   0.9855   0.1105
  -4.500  -0.2104   0.07507   0.07124  -0.0421   0.9767   0.1163
  -4.250  -0.1487   0.07042   0.06642  -0.0592   0.9680   0.1280
  -4.000  -0.1298   0.06674   0.06278  -0.0569   0.9613   0.1320
  -3.750  -0.0756   0.06207   0.05796  -0.0693   0.9519   0.1434
  -3.500   0.0398   0.04313   0.03805  -0.1026   0.9500   0.0873
  -3.250   0.0967   0.03740   0.03205  -0.1110   0.9459   0.0839
  -3.000   0.1755   0.02730   0.02040  -0.1249   0.9461   0.0834
  -2.750   0.2220   0.02500   0.01761  -0.1286   0.9368   0.0922
  -2.500   0.2719   0.02348   0.01582  -0.1324   0.9293   0.1056
  -2.250   0.3165   0.02262   0.01479  -0.1349   0.9191   0.1284
  -2.000   0.3544   0.02268   0.01498  -0.1360   0.9068   0.1619
  -1.750   0.3918   0.02269   0.01497  -0.1371   0.8960   0.2171
  -1.500   0.4358   0.02229   0.01460  -0.1396   0.8899   0.2500
  -1.250   0.4712   0.02197   0.01418  -0.1406   0.8788   0.2756
  -1.000   0.5087   0.02146   0.01373  -0.1419   0.8690   0.2972
  -0.750   0.5543   0.02050   0.01254  -0.1446   0.8615   0.3076
  -0.500   0.5915   0.01978   0.01171  -0.1458   0.8494   0.3127
  -0.250   0.6304   0.01914   0.01086  -0.1473   0.8370   0.3194
   0.000   0.6680   0.01853   0.01019  -0.1485   0.8236   0.3268
   0.250   0.7040   0.01810   0.00959  -0.1494   0.8083   0.3343
   0.500   0.7372   0.01775   0.00917  -0.1497   0.7915   0.3414
   0.750   0.7687   0.01756   0.00883  -0.1498   0.7737   0.3511
   1.000   0.7985   0.01740   0.00860  -0.1495   0.7556   0.3626
   1.250   0.8245   0.01732   0.00848  -0.1485   0.7362   0.3743
   1.500   0.8508   0.01726   0.00837  -0.1477   0.7170   0.3880
   1.750   0.8772   0.01718   0.00824  -0.1468   0.6983   0.4074
   2.000   0.9033   0.01702   0.00812  -0.1460   0.6800   0.4367
   2.250   0.9271   0.01667   0.00813  -0.1448   0.6604   0.5142
   2.500   0.9501   0.01609   0.00799  -0.1431   0.6400   1.0000
   2.750   0.9757   0.01632   0.00796  -0.1421   0.6199   1.0000
   3.000   1.0000   0.01661   0.00806  -0.1410   0.5992   1.0000
   3.250   1.0245   0.01693   0.00823  -0.1400   0.5796   1.0000
   3.500   1.0494   0.01729   0.00845  -0.1392   0.5619   1.0000
   3.750   1.0743   0.01768   0.00869  -0.1384   0.5453   1.0000
   4.000   1.0989   0.01808   0.00896  -0.1376   0.5292   1.0000
   4.250   1.1232   0.01848   0.00925  -0.1367   0.5138   1.0000
   4.500   1.1471   0.01888   0.00961  -0.1358   0.4989   1.0000
   4.750   1.1709   0.01930   0.00998  -0.1349   0.4850   1.0000
   5.000   1.1945   0.01971   0.01038  -0.1340   0.4717   1.0000
   5.250   1.2182   0.02014   0.01080  -0.1332   0.4595   1.0000
   5.500   1.2423   0.02059   0.01125  -0.1324   0.4484   1.0000
   5.750   1.2668   0.02104   0.01165  -0.1317   0.4378   1.0000
   6.000   1.2896   0.02152   0.01221  -0.1308   0.4266   1.0000
   6.250   1.3131   0.02204   0.01280  -0.1300   0.4164   1.0000
   6.500   1.3377   0.02256   0.01329  -0.1293   0.4069   1.0000
   6.750   1.3599   0.02312   0.01395  -0.1283   0.3962   1.0000
   7.000   1.3826   0.02374   0.01465  -0.1274   0.3860   1.0000
   7.250   1.4068   0.02439   0.01530  -0.1268   0.3764   1.0000
   7.500   1.4288   0.02507   0.01610  -0.1258   0.3660   1.0000
   7.750   1.4507   0.02586   0.01701  -0.1248   0.3561   1.0000
   8.000   1.4758   0.02665   0.01777  -0.1244   0.3473   1.0000
   8.250   1.4946   0.02730   0.01861  -0.1229   0.3358   1.0000
   8.500   1.5116   0.02781   0.01923  -0.1210   0.3228   1.0000
   8.750   1.5274   0.02824   0.01976  -0.1190   0.3096   1.0000
   9.000   1.5433   0.02868   0.02030  -0.1170   0.2977   1.0000
   9.250   1.5593   0.02907   0.02076  -0.1150   0.2865   1.0000
   9.500   1.5702   0.02940   0.02132  -0.1122   0.2739   1.0000
   9.750   1.5787   0.02972   0.02188  -0.1091   0.2601   1.0000
  10.000   1.5863   0.03010   0.02248  -0.1058   0.2455   1.0000
  10.250   1.5887   0.03056   0.02311  -0.1018   0.2248   1.0000
  10.500   1.5857   0.03149   0.02402  -0.0973   0.1974   1.0000
  10.750   1.5758   0.03340   0.02573  -0.0926   0.1665   1.0000
  11.250   1.5390   0.04006   0.03178  -0.0839   0.0832   1.0000
  11.500   1.5179   0.04420   0.03594  -0.0807   0.0756   1.0000
  11.750   1.5037   0.04813   0.04007  -0.0786   0.0680   1.0000
  12.000   1.4870   0.05261   0.04467  -0.0773   0.0640   1.0000
  12.250   1.4756   0.05682   0.04905  -0.0765   0.0599   1.0000
  12.500   1.4653   0.06108   0.05348  -0.0761   0.0563   1.0000
  12.750   1.4532   0.06575   0.05826  -0.0762   0.0538   1.0000
  13.000   1.4402   0.07063   0.06323  -0.0764   0.0520   1.0000
  13.250   1.4328   0.07493   0.06770  -0.0766   0.0496   1.0000
  13.500   1.4252   0.07931   0.07223  -0.0770   0.0476   1.0000
  13.750   1.4183   0.08361   0.07661  -0.0773   0.0459   1.0000
  14.000   1.4133   0.08746   0.08051  -0.0773   0.0445   1.0000
  14.250   1.4170   0.08940   0.08235  -0.0754   0.0428   1.0000
  14.500   1.4266   0.09082   0.08389  -0.0733   0.0415   1.0000
  14.750   1.4365   0.09242   0.08559  -0.0713   0.0402   1.0000
  15.000   1.4422   0.09486   0.08815  -0.0702   0.0388   1.0000
  15.250   1.4456   0.09773   0.09113  -0.0696   0.0375   1.0000
  15.500   1.4502   0.10042   0.09386  -0.0689   0.0362   1.0000
  15.750   1.4604   0.10260   0.09612  -0.0671   0.0353   1.0000
  16.000   1.4636   0.10620   0.09995  -0.0665   0.0350   1.0000
  16.250   1.4585   0.11096   0.10495  -0.0673   0.0350   1.0000
  16.500   1.4477   0.11654   0.11079  -0.0694   0.0350   1.0000
  16.750   1.4340   0.12275   0.11726  -0.0725   0.0352   1.0000
  17.000   1.4171   0.12983   0.12462  -0.0767   0.0354   1.0000
  17.250   1.3958   0.13827   0.13337  -0.0823   0.0358   1.0000
  17.500   1.3697   0.14855   0.14396  -0.0896   0.0365   1.0000
  17.750   1.3300   0.16338   0.15910  -0.1010   0.0376   1.0000
  18.000   1.2739   0.18580   0.18175  -0.1179   0.0402   1.0000
  18.250   1.2508   0.19996   0.19591  -0.1271   0.0421   1.0000
  18.500   1.2438   0.20887   0.20480  -0.1322   0.0428   1.0000
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