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

FX 76-MP-160 (fx76mp160-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 76-MP-160 (fx76mp160-il)
Reynolds number: 200,000
Max Cl/Cd: 71.98 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76mp160-il-200000-n5.txt
Download as CSV file: xf-fx76mp160-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 76-MP-160                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2245   0.04237   0.03668  -0.1790   0.8390   0.0330
 -11.500  -0.2501   0.03765   0.03177  -0.1815   0.8343   0.0330
 -11.250  -0.2686   0.03461   0.02854  -0.1815   0.8300   0.0332
 -11.000  -0.2810   0.03270   0.02646  -0.1798   0.8264   0.0333
 -10.750  -0.2869   0.03106   0.02460  -0.1783   0.8235   0.0335
 -10.500  -0.2829   0.02954   0.02279  -0.1773   0.8213   0.0339
 -10.250  -0.2745   0.02843   0.02158  -0.1760   0.8189   0.0343
 -10.000  -0.2623   0.02760   0.02071  -0.1748   0.8164   0.0347
  -9.750  -0.2481   0.02678   0.01983  -0.1739   0.8140   0.0352
  -9.500  -0.2322   0.02593   0.01889  -0.1730   0.8115   0.0359
  -9.250  -0.2144   0.02510   0.01792  -0.1724   0.8091   0.0368
  -9.000  -0.1948   0.02425   0.01689  -0.1720   0.8069   0.0379
  -8.750  -0.1738   0.02343   0.01587  -0.1717   0.8051   0.0392
  -8.500  -0.1515   0.02275   0.01518  -0.1715   0.8035   0.0403
  -8.250  -0.1283   0.02217   0.01453  -0.1714   0.8020   0.0418
  -8.000  -0.1093   0.02165   0.01393  -0.1705   0.7997   0.0433
  -7.750  -0.0891   0.02113   0.01337  -0.1697   0.7974   0.0449
  -7.500  -0.0670   0.02076   0.01301  -0.1692   0.7951   0.0465
  -7.250  -0.0437   0.02041   0.01260  -0.1688   0.7928   0.0484
  -7.000  -0.0192   0.02002   0.01214  -0.1685   0.7904   0.0503
  -6.750   0.0070   0.01972   0.01180  -0.1685   0.7882   0.0524
  -6.500   0.0342   0.01940   0.01139  -0.1686   0.7863   0.0548
  -6.250   0.0619   0.01911   0.01102  -0.1689   0.7847   0.0572
  -6.000   0.0898   0.01885   0.01069  -0.1691   0.7834   0.0599
  -5.750   0.1104   0.01874   0.01053  -0.1680   0.7806   0.0625
  -5.500   0.1324   0.01853   0.01035  -0.1673   0.7776   0.0651
  -5.250   0.1566   0.01832   0.01010  -0.1668   0.7748   0.0683
  -5.000   0.1822   0.01805   0.00982  -0.1666   0.7723   0.0718
  -4.750   0.2092   0.01779   0.00956  -0.1667   0.7700   0.0760
  -4.500   0.2375   0.01754   0.00932  -0.1669   0.7680   0.0813
  -4.250   0.2670   0.01732   0.00908  -0.1674   0.7663   0.0875
  -4.000   0.2972   0.01713   0.00883  -0.1679   0.7647   0.0955
  -3.750   0.3178   0.01709   0.00885  -0.1667   0.7613   0.1022
  -3.500   0.3395   0.01705   0.00883  -0.1658   0.7578   0.1090
  -3.250   0.3643   0.01694   0.00874  -0.1653   0.7546   0.1167
  -3.000   0.3913   0.01679   0.00863  -0.1653   0.7518   0.1267
  -2.750   0.4200   0.01665   0.00846  -0.1655   0.7495   0.1390
  -2.500   0.4502   0.01646   0.00825  -0.1659   0.7475   0.1498
  -2.250   0.4815   0.01625   0.00806  -0.1666   0.7457   0.1618
  -2.000   0.5030   0.01626   0.00815  -0.1656   0.7418   0.1749
  -1.750   0.5226   0.01632   0.00824  -0.1642   0.7369   0.1897
  -1.500   0.5482   0.01620   0.00816  -0.1638   0.7332   0.2052
  -1.000   0.6069   0.01585   0.00791  -0.1645   0.7283   0.2481
  -0.750   0.6387   0.01562   0.00774  -0.1653   0.7263   0.2711
  -0.500   0.6550   0.01573   0.00797  -0.1633   0.7209   0.3006
  -0.250   0.6765   0.01563   0.00801  -0.1622   0.7158   0.3323
   0.000   0.7042   0.01537   0.00790  -0.1622   0.7121   0.3868
   0.250   0.7349   0.01489   0.00771  -0.1628   0.7090   0.4767
   0.500   0.7591   0.01464   0.00778  -0.1620   0.7053   0.5777
   0.750   0.7698   0.01479   0.00824  -0.1585   0.6990   0.6540
   1.000   0.7918   0.01480   0.00833  -0.1571   0.6945   0.7078
   1.250   0.8202   0.01471   0.00821  -0.1569   0.6908   0.7393
   1.500   0.8484   0.01464   0.00810  -0.1568   0.6868   0.7585
   1.750   0.8564   0.01491   0.00845  -0.1530   0.6786   0.7717
   2.000   0.8811   0.01484   0.00835  -0.1521   0.6728   0.7879
   2.250   0.9065   0.01477   0.00824  -0.1514   0.6672   0.8007
   2.500   0.9140   0.01496   0.00849  -0.1475   0.6589   0.8117
   2.750   0.9394   0.01484   0.00835  -0.1467   0.6533   0.8233
   3.000   0.9569   0.01491   0.00843  -0.1447   0.6465   0.8354
   3.250   0.9728   0.01502   0.00853  -0.1423   0.6385   0.8485
   3.500   1.0024   0.01482   0.00827  -0.1423   0.6318   0.8609
   3.750   1.0081   0.01513   0.00863  -0.1382   0.6210   0.8718
   4.000   1.0335   0.01505   0.00850  -0.1376   0.6118   0.8827
   4.250   1.0452   0.01533   0.00879  -0.1348   0.6002   0.8953
   4.500   1.0681   0.01536   0.00879  -0.1339   0.5899   0.9058
   4.750   1.0905   0.01548   0.00886  -0.1331   0.5784   0.9185
   5.250   1.1373   0.01580   0.00910  -0.1321   0.5555   1.0000
   5.500   1.1542   0.01623   0.00950  -0.1306   0.5428   1.0000
   5.750   1.1733   0.01662   0.00981  -0.1295   0.5302   1.0000
   6.000   1.1916   0.01705   0.01013  -0.1282   0.5176   1.0000
   6.250   1.2075   0.01759   0.01060  -0.1267   0.5047   1.0000
   6.500   1.2236   0.01814   0.01105  -0.1252   0.4925   1.0000
   6.750   1.2375   0.01878   0.01167  -0.1235   0.4795   1.0000
   7.000   1.2519   0.01942   0.01226  -0.1219   0.4674   1.0000
   7.250   1.2662   0.02009   0.01285  -0.1203   0.4561   1.0000
   7.500   1.2802   0.02079   0.01352  -0.1187   0.4449   1.0000
   7.750   1.2933   0.02155   0.01420  -0.1170   0.4340   1.0000
   8.000   1.3066   0.02233   0.01499  -0.1154   0.4226   1.0000
   8.250   1.3187   0.02317   0.01578  -0.1137   0.4111   1.0000
   8.500   1.3302   0.02406   0.01663  -0.1120   0.3992   1.0000
   8.750   1.3414   0.02499   0.01751  -0.1103   0.3876   1.0000
   9.000   1.3533   0.02591   0.01839  -0.1087   0.3785   1.0000
   9.250   1.3663   0.02680   0.01928  -0.1073   0.3689   1.0000
   9.500   1.3787   0.02773   0.02020  -0.1059   0.3599   1.0000
   9.750   1.3912   0.02868   0.02114  -0.1045   0.3513   1.0000
  10.000   1.4033   0.02967   0.02214  -0.1031   0.3417   1.0000
  10.250   1.4139   0.03076   0.02322  -0.1016   0.3329   1.0000
  10.500   1.4238   0.03191   0.02435  -0.1002   0.3230   1.0000
  10.750   1.4338   0.03309   0.02549  -0.0987   0.3151   1.0000
  11.000   1.4466   0.03414   0.02659  -0.0976   0.3072   1.0000
  11.250   1.4557   0.03543   0.02787  -0.0961   0.2987   1.0000
  11.500   1.4679   0.03655   0.02903  -0.0951   0.2910   1.0000
  11.750   1.4787   0.03778   0.03030  -0.0939   0.2832   1.0000
  12.000   1.4875   0.03918   0.03169  -0.0926   0.2757   1.0000
  12.250   1.4981   0.04048   0.03303  -0.0915   0.2684   1.0000
  12.500   1.5051   0.04207   0.03460  -0.0902   0.2611   1.0000
  12.750   1.5149   0.04348   0.03606  -0.0892   0.2543   1.0000
  13.000   1.5250   0.04491   0.03753  -0.0882   0.2475   1.0000
  13.250   1.5312   0.04666   0.03927  -0.0870   0.2408   1.0000
  13.500   1.5417   0.04812   0.04083  -0.0862   0.2342   1.0000
  13.750   1.5505   0.04973   0.04250  -0.0853   0.2274   1.0000
  14.000   1.5562   0.05163   0.04441  -0.0843   0.2216   1.0000
  14.250   1.5652   0.05328   0.04614  -0.0836   0.2159   1.0000
  14.500   1.5717   0.05518   0.04808  -0.0827   0.2101   1.0000
  14.750   1.5749   0.05742   0.05032  -0.0818   0.2047   1.0000
  15.000   1.5833   0.05924   0.05225  -0.0812   0.1988   1.0000
  15.250   1.5885   0.06139   0.05447  -0.0806   0.1927   1.0000
  15.500   1.5899   0.06394   0.05702  -0.0798   0.1866   1.0000
  15.750   1.5964   0.06604   0.05925  -0.0794   0.1800   1.0000
  16.000   1.5981   0.06870   0.06196  -0.0789   0.1727   1.0000
  16.250   1.5989   0.07151   0.06481  -0.0785   0.1661   1.0000
  16.500   1.5992   0.07443   0.06778  -0.0782   0.1596   1.0000
  16.750   1.5960   0.07781   0.07116  -0.0780   0.1541   1.0000
  17.000   1.5999   0.08037   0.07384  -0.0779   0.1491   1.0000
  17.250   1.6001   0.08343   0.07699  -0.0779   0.1436   1.0000
  17.500   1.5980   0.08682   0.08042  -0.0779   0.1388   1.0000
  17.750   1.5990   0.08987   0.08358  -0.0781   0.1342   1.0000
  18.000   1.5989   0.09312   0.08693  -0.0784   0.1286   1.0000
  18.250   1.5941   0.09703   0.09087  -0.0789   0.1234   1.0000
  18.500   1.5916   0.10066   0.09458  -0.0795   0.1185   1.0000
  18.750   1.5872   0.10459   0.09857  -0.0803   0.1136   1.0000
<< Back to FX 76-MP-160 (fx76mp160-il)

Polar data table (+)

Polar graphs


<< Back to FX 76-MP-160 (fx76mp160-il)