Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)
Reynolds number: 1,000,000
Max Cl/Cd: 153.32 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx62k131-il-1000000-n5.txt
Download as CSV file: xf-fx62k131-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 62-K-131 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1072   0.09452   0.09218  -0.0916   0.8289   0.0025
 -11.250  -0.1084   0.09010   0.08774  -0.0927   0.8264   0.0024
 -10.750  -0.2158   0.09656   0.09415  -0.0878   0.8386   0.0021
 -10.500  -0.2143   0.09196   0.08955  -0.0900   0.8349   0.0021
 -10.250  -0.2130   0.08736   0.08495  -0.0924   0.8311   0.0021
 -10.000  -0.2123   0.08265   0.08024  -0.0951   0.8274   0.0021
  -9.500  -0.2123   0.07264   0.07023  -0.1018   0.8207   0.0021
  -9.250  -0.2152   0.06636   0.06397  -0.1068   0.8169   0.0022
  -9.000  -0.2311   0.05465   0.05224  -0.1198   0.8121   0.0021
  -8.750  -0.2477   0.04690   0.04434  -0.1278   0.8077   0.0021
  -8.500  -0.2467   0.04077   0.03800  -0.1339   0.8041   0.0022
  -8.250  -0.2368   0.03613   0.03313  -0.1369   0.8009   0.0023
  -8.000  -0.2229   0.03156   0.02828  -0.1391   0.7980   0.0024
  -7.750  -0.2072   0.02580   0.02209  -0.1411   0.7954   0.0027
  -7.500  -0.1895   0.01811   0.01362  -0.1428   0.7931   0.0030
  -7.250  -0.1636   0.01588   0.01104  -0.1436   0.7909   0.0031
  -7.000  -0.1365   0.01449   0.00943  -0.1442   0.7886   0.0032
  -6.750  -0.1088   0.01362   0.00841  -0.1448   0.7863   0.0034
  -6.500  -0.0806   0.01298   0.00765  -0.1454   0.7842   0.0036
  -6.250  -0.0521   0.01251   0.00709  -0.1460   0.7822   0.0038
  -6.000  -0.0233   0.01197   0.00646  -0.1466   0.7802   0.0039
  -5.750   0.0067   0.01078   0.00513  -0.1479   0.7781   0.0041
  -5.500   0.0373   0.01022   0.00449  -0.1491   0.7759   0.0045
  -5.250   0.0678   0.00987   0.00410  -0.1501   0.7736   0.0049
  -5.000   0.0985   0.00957   0.00375  -0.1511   0.7711   0.0055
  -4.750   0.1292   0.00931   0.00342  -0.1521   0.7682   0.0061
  -4.500   0.1599   0.00907   0.00315  -0.1531   0.7650   0.0065
  -4.250   0.1920   0.00872   0.00275  -0.1544   0.7617   0.0077
  -4.000   0.2228   0.00855   0.00256  -0.1554   0.7590   0.0093
  -3.750   0.2537   0.00839   0.00237  -0.1563   0.7566   0.0105
  -3.500   0.2850   0.00820   0.00215  -0.1573   0.7543   0.0143
  -3.250   0.3160   0.00805   0.00200  -0.1583   0.7521   0.0207
  -3.000   0.3484   0.00781   0.00186  -0.1597   0.7496   0.0509
  -2.750   0.3826   0.00747   0.00172  -0.1617   0.7470   0.1205
  -2.500   0.4280   0.00657   0.00151  -0.1670   0.7445   0.3516
  -2.250   0.4729   0.00593   0.00139  -0.1718   0.7420   0.5373
  -2.000   0.5069   0.00581   0.00139  -0.1735   0.7394   0.5974
  -1.750   0.5391   0.00575   0.00142  -0.1747   0.7364   0.6395
  -1.500   0.5693   0.00575   0.00143  -0.1753   0.7332   0.6540
  -1.250   0.5991   0.00577   0.00142  -0.1759   0.7300   0.6613
  -1.000   0.6286   0.00580   0.00144  -0.1764   0.7268   0.6677
  -0.750   0.6584   0.00582   0.00144  -0.1770   0.7235   0.6732
  -0.500   0.6880   0.00584   0.00147  -0.1775   0.7196   0.6777
  -0.250   0.7172   0.00588   0.00149  -0.1780   0.7149   0.6825
   0.000   0.7463   0.00592   0.00150  -0.1784   0.7089   0.6880
   0.250   0.7750   0.00597   0.00155  -0.1788   0.7013   0.6928
   0.500   0.8039   0.00602   0.00159  -0.1791   0.6949   0.6974
   0.750   0.8328   0.00607   0.00162  -0.1796   0.6887   0.7023
   1.000   0.8613   0.00613   0.00169  -0.1799   0.6824   0.7067
   1.250   0.8897   0.00620   0.00176  -0.1802   0.6744   0.7110
   1.500   0.9181   0.00628   0.00182  -0.1805   0.6658   0.7148
   1.750   0.9461   0.00637   0.00189  -0.1807   0.6561   0.7178
   2.000   0.9739   0.00647   0.00198  -0.1809   0.6455   0.7204
   2.250   1.0015   0.00658   0.00209  -0.1810   0.6340   0.7232
   2.500   1.0288   0.00671   0.00219  -0.1811   0.6209   0.7259
   2.750   1.0554   0.00689   0.00231  -0.1810   0.6047   0.7287
   3.000   1.0804   0.00716   0.00248  -0.1807   0.5780   0.7313
   3.250   1.1025   0.00762   0.00276  -0.1798   0.5359   0.7335
   3.500   1.1232   0.00817   0.00309  -0.1786   0.4871   0.7358
   3.750   1.1453   0.00865   0.00339  -0.1778   0.4470   0.7383
   4.000   1.1661   0.00921   0.00373  -0.1767   0.4002   0.7408
   4.250   1.1849   0.00990   0.00417  -0.1753   0.3474   0.7433
   4.500   1.2045   0.01053   0.00459  -0.1741   0.3025   0.7455
   4.750   1.2169   0.01161   0.00525  -0.1716   0.2235   0.7476
   5.000   1.2289   0.01268   0.00594  -0.1690   0.1522   0.7497
   5.250   1.2424   0.01361   0.00660  -0.1667   0.0988   0.7518
   5.500   1.2579   0.01438   0.00718  -0.1647   0.0628   0.7542
   5.750   1.2747   0.01503   0.00772  -0.1630   0.0391   0.7565
   6.000   1.2895   0.01567   0.00826  -0.1608   0.0217   0.7586
   6.250   1.3044   0.01620   0.00877  -0.1586   0.0129   0.7605
   6.500   1.3188   0.01684   0.00938  -0.1564   0.0045   0.7624
   6.750   1.3346   0.01742   0.00999  -0.1545   0.0026   0.7644
   7.000   1.3510   0.01796   0.01059  -0.1527   0.0022   0.7664
   7.250   1.3664   0.01858   0.01126  -0.1508   0.0018   0.7683
   7.500   1.3814   0.01924   0.01198  -0.1489   0.0015   0.7702
   7.750   1.3977   0.01984   0.01265  -0.1473   0.0015   0.7721
   8.000   1.4131   0.02051   0.01337  -0.1456   0.0014   0.7740
   8.250   1.4276   0.02125   0.01419  -0.1438   0.0013   0.7757
   8.500   1.4417   0.02204   0.01504  -0.1421   0.0013   0.7774
   8.750   1.4549   0.02291   0.01598  -0.1402   0.0012   0.7791
   9.000   1.4678   0.02382   0.01696  -0.1384   0.0011   0.7810
   9.250   1.4800   0.02482   0.01804  -0.1365   0.0011   0.7829
   9.500   1.4919   0.02585   0.01913  -0.1348   0.0010   0.7847
   9.750   1.5027   0.02701   0.02036  -0.1329   0.0010   0.7864
  10.000   1.5134   0.02818   0.02161  -0.1311   0.0009   0.7880
  10.250   1.5237   0.02942   0.02295  -0.1293   0.0009   0.7896
  10.500   1.5335   0.03068   0.02430  -0.1275   0.0008   0.7912
  10.750   1.5420   0.03211   0.02581  -0.1257   0.0008   0.7928
  11.000   1.5491   0.03366   0.02745  -0.1237   0.0007   0.7945
  11.250   1.5552   0.03532   0.02921  -0.1218   0.0007   0.7962
  11.500   1.5588   0.03722   0.03121  -0.1196   0.0007   0.7979
  11.750   1.5485   0.04045   0.03462  -0.1162   0.0006   0.7993
  12.000   1.5538   0.04226   0.03653  -0.1145   0.0006   0.8008
  12.250   1.5576   0.04425   0.03862  -0.1128   0.0006   0.8023
  12.500   1.5626   0.04618   0.04066  -0.1113   0.0005   0.8037
  12.750   1.5658   0.04835   0.04294  -0.1098   0.0005   0.8051
  13.000   1.5674   0.05073   0.04544  -0.1082   0.0005   0.8064
  13.250   1.5680   0.05326   0.04809  -0.1068   0.0005   0.8078
  13.500   1.5679   0.05595   0.05092  -0.1054   0.0005   0.8094
  13.750   1.5678   0.05874   0.05383  -0.1042   0.0005   0.8109
  14.000   1.5657   0.06182   0.05704  -0.1031   0.0005   0.8124
  14.250   1.5627   0.06512   0.06048  -0.1022   0.0005   0.8138
  14.500   1.5588   0.06859   0.06408  -0.1014   0.0005   0.8150
  14.750   1.5537   0.07237   0.06800  -0.1008   0.0005   0.8161
  15.000   1.5473   0.07646   0.07225  -0.1005   0.0004   0.8172
  15.250   1.5397   0.08080   0.07675  -0.1004   0.0004   0.8185
  15.500   1.5306   0.08549   0.08159  -0.1005   0.0004   0.8198
  15.750   1.5208   0.09044   0.08671  -0.1010   0.0004   0.8211
  16.000   1.5110   0.09556   0.09197  -0.1018   0.0004   0.8224
  16.250   1.4992   0.10116   0.09774  -0.1030   0.0004   0.8237
  16.500   1.4859   0.10719   0.10393  -0.1046   0.0004   0.8248
  16.750   1.4738   0.11313   0.11002  -0.1065   0.0004   0.8260
  17.000   1.4582   0.11995   0.11700  -0.1091   0.0004   0.8270
  17.250   1.4441   0.12672   0.12392  -0.1119   0.0004   0.8280
  17.500   1.4300   0.13375   0.13111  -0.1153   0.0004   0.8290
  18.000   1.4003   0.14893   0.14659  -0.1234   0.0004   0.8308
  18.250   1.3854   0.15691   0.15472  -0.1281   0.0004   0.8319
  18.500   1.3678   0.16600   0.16396  -0.1337   0.0004   0.8328
  18.750   1.3530   0.17485   0.17295  -0.1394   0.0004   0.8338
<< Back to WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il)