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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 500,000
Max Cl/Cd: 91.97 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe164-il-500000-n5.txt
Download as CSV file: xf-goe164-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1430   0.11031   0.10814  -0.0484   0.9895   0.0106
 -10.500  -0.2924   0.12541   0.12314  -0.0280   0.9992   0.0094
 -10.250  -0.2818   0.12087   0.11862  -0.0310   0.9981   0.0095
 -10.000  -0.2646   0.11775   0.11550  -0.0333   0.9968   0.0099
  -9.500  -0.1033   0.08974   0.08757  -0.0589   0.9816   0.0090
  -9.000  -0.2094   0.10160   0.09933  -0.0474   0.9897   0.0091
  -8.750  -0.1936   0.09835   0.09608  -0.0504   0.9881   0.0087
  -8.500  -0.1780   0.09446   0.09219  -0.0543   0.9861   0.0083
  -8.250  -0.1667   0.09072   0.08846  -0.0571   0.9819   0.0080
  -8.000  -0.1518   0.08647   0.08421  -0.0614   0.9789   0.0078
  -7.750  -0.1404   0.08246   0.08022  -0.0647   0.9737   0.0076
  -7.500  -0.1277   0.07834   0.07611  -0.0687   0.9682   0.0076
  -7.250  -0.1180   0.07445   0.07223  -0.0718   0.9602   0.0076
  -7.000  -0.0985   0.06954   0.06731  -0.0783   0.9545   0.0077
  -6.500  -0.0275   0.01944   0.01584  -0.1453   0.9184   0.0083
  -6.250   0.0115   0.01653   0.01242  -0.1496   0.9068   0.0087
  -6.000   0.0571   0.01465   0.01013  -0.1542   0.8931   0.0091
  -5.500   0.1461   0.01222   0.00694  -0.1619   0.8316   0.0104
  -5.250   0.1748   0.01184   0.00629  -0.1621   0.8063   0.0111
  -5.000   0.2021   0.01154   0.00578  -0.1619   0.7880   0.0121
  -4.750   0.2293   0.01126   0.00532  -0.1617   0.7718   0.0131
  -4.500   0.2564   0.01078   0.00464  -0.1615   0.7550   0.0145
  -4.250   0.2834   0.01054   0.00426  -0.1612   0.7391   0.0160
  -4.000   0.3102   0.01036   0.00392  -0.1608   0.7223   0.0178
  -3.750   0.3369   0.01016   0.00359  -0.1605   0.7050   0.0208
  -3.500   0.3635   0.01005   0.00336  -0.1601   0.6879   0.0246
  -3.250   0.3903   0.00991   0.00310  -0.1597   0.6703   0.0285
  -3.000   0.4170   0.00983   0.00292  -0.1593   0.6522   0.0338
  -2.750   0.4438   0.00975   0.00272  -0.1590   0.6353   0.0382
  -2.500   0.4708   0.00966   0.00253  -0.1586   0.6194   0.0446
  -2.250   0.4976   0.00962   0.00237  -0.1583   0.6031   0.0514
  -2.000   0.5244   0.00947   0.00220  -0.1580   0.5863   0.0734
  -1.750   0.5508   0.00940   0.00220  -0.1577   0.5690   0.1281
  -1.500   0.5770   0.00953   0.00221  -0.1572   0.5486   0.1403
  -1.250   0.6030   0.00967   0.00223  -0.1567   0.5258   0.1484
  -1.000   0.6289   0.00984   0.00225  -0.1562   0.5034   0.1544
  -0.750   0.6551   0.00999   0.00226  -0.1558   0.4813   0.1593
  -0.500   0.6810   0.01016   0.00232  -0.1553   0.4566   0.1648
  -0.250   0.7065   0.01038   0.00238  -0.1547   0.4256   0.1706
   0.000   0.7319   0.01062   0.00246  -0.1542   0.3953   0.1764
   0.250   0.7574   0.01083   0.00254  -0.1537   0.3705   0.1798
   0.500   0.7833   0.01102   0.00262  -0.1533   0.3530   0.1827
   0.750   0.8095   0.01118   0.00270  -0.1529   0.3402   0.1861
   1.000   0.8358   0.01132   0.00278  -0.1525   0.3303   0.1892
   1.250   0.8620   0.01145   0.00287  -0.1522   0.3218   0.1927
   1.500   0.8886   0.01155   0.00296  -0.1519   0.3149   0.1962
   1.750   0.9149   0.01168   0.00306  -0.1516   0.3084   0.1999
   2.000   0.9414   0.01180   0.00316  -0.1512   0.3030   0.2034
   2.250   0.9677   0.01191   0.00327  -0.1509   0.2966   0.2077
   2.500   0.9938   0.01205   0.00341  -0.1506   0.2900   0.2130
   3.000   1.0457   0.01234   0.00368  -0.1498   0.2718   0.2251
   3.250   1.0712   0.01253   0.00385  -0.1494   0.2603   0.2322
   3.500   1.0967   0.01270   0.00401  -0.1490   0.2483   0.2421
   3.750   1.1217   0.01292   0.00421  -0.1485   0.2310   0.2568
   4.000   1.1431   0.01348   0.00458  -0.1475   0.1860   0.2859
   4.250   1.1674   0.01373   0.00491  -0.1470   0.1761   0.3477
   4.500   1.1921   0.01392   0.00518  -0.1465   0.1707   0.3977
   4.750   1.2118   0.01325   0.00550  -0.1449   0.1665   1.0000
   5.000   1.2366   0.01350   0.00575  -0.1444   0.1636   1.0000
   5.250   1.2613   0.01373   0.00599  -0.1438   0.1613   1.0000
   5.500   1.2858   0.01398   0.00625  -0.1432   0.1590   1.0000
   5.750   1.3100   0.01425   0.00653  -0.1426   0.1567   1.0000
   6.000   1.3339   0.01453   0.00683  -0.1419   0.1544   1.0000
   6.250   1.3574   0.01482   0.00714  -0.1412   0.1521   1.0000
   6.500   1.3809   0.01512   0.00746  -0.1404   0.1490   1.0000
   6.750   1.4041   0.01542   0.00778  -0.1397   0.1413   1.0000
   7.000   1.4260   0.01582   0.00815  -0.1387   0.1318   1.0000
   7.250   1.4421   0.01669   0.00876  -0.1369   0.0892   1.0000
   7.500   1.4608   0.01731   0.00936  -0.1354   0.0819   1.0000
   7.750   1.4813   0.01775   0.00984  -0.1342   0.0778   1.0000
   8.000   1.4995   0.01835   0.01048  -0.1326   0.0722   1.0000
   8.250   1.5189   0.01882   0.01101  -0.1313   0.0674   1.0000
   8.500   1.5342   0.01947   0.01161  -0.1292   0.0468   1.0000
   8.750   1.5377   0.02092   0.01286  -0.1253   0.0161   1.0000
   9.000   1.5504   0.02170   0.01368  -0.1229   0.0126   1.0000
   9.250   1.5641   0.02241   0.01447  -0.1207   0.0109   1.0000
   9.500   1.5772   0.02316   0.01530  -0.1184   0.0098   1.0000
   9.750   1.5883   0.02403   0.01624  -0.1160   0.0088   1.0000
  10.000   1.5977   0.02504   0.01736  -0.1134   0.0079   1.0000
  10.250   1.6087   0.02594   0.01835  -0.1111   0.0073   1.0000
  10.500   1.6180   0.02699   0.01948  -0.1087   0.0068   1.0000
  10.750   1.6260   0.02815   0.02073  -0.1063   0.0064   1.0000
  11.000   1.6321   0.02950   0.02217  -0.1038   0.0061   1.0000
  11.250   1.6348   0.03118   0.02395  -0.1011   0.0058   1.0000
  11.500   1.6368   0.03301   0.02590  -0.0987   0.0055   1.0000
  11.750   1.6406   0.03479   0.02780  -0.0967   0.0053   1.0000
  12.000   1.6433   0.03678   0.02990  -0.0949   0.0051   1.0000
  12.250   1.6448   0.03903   0.03226  -0.0934   0.0049   1.0000
  12.500   1.6454   0.04148   0.03485  -0.0921   0.0047   1.0000
  12.750   1.6446   0.04419   0.03768  -0.0910   0.0045   1.0000
  13.000   1.6428   0.04714   0.04074  -0.0901   0.0043   1.0000
  13.250   1.6392   0.05042   0.04414  -0.0895   0.0042   1.0000
  13.500   1.6326   0.05420   0.04803  -0.0890   0.0041   1.0000
  13.750   1.6231   0.05852   0.05249  -0.0889   0.0040   1.0000
  14.000   1.6114   0.06335   0.05746  -0.0891   0.0039   1.0000
  14.250   1.5975   0.06862   0.06287  -0.0896   0.0039   1.0000
  14.500   1.5875   0.07352   0.06790  -0.0902   0.0038   1.0000
  14.750   1.5762   0.07872   0.07325  -0.0911   0.0038   1.0000
  15.000   1.5642   0.08414   0.07880  -0.0921   0.0037   1.0000
  15.250   1.5520   0.08969   0.08448  -0.0933   0.0037   1.0000
  15.500   1.5398   0.09533   0.09025  -0.0947   0.0037   1.0000
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