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=100,000 Ncrit=5


Details Polar file
Airfoil: FX 76-MP-160 (fx76mp160-il)
Reynolds number: 100,000
Max Cl/Cd: 40.1 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76mp160-il-100000-n5.txt
Download as CSV file: xf-fx76mp160-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750   0.0253   0.10263   0.09643  -0.1376   0.9000   0.0498
 -11.500   0.0346   0.09919   0.09297  -0.1400   0.8972   0.0496
 -11.250   0.0370   0.09442   0.08817  -0.1436   0.8945   0.0499
 -11.000   0.0483   0.09156   0.08530  -0.1457   0.8918   0.0503
 -10.750   0.0562   0.09004   0.08379  -0.1456   0.8877   0.0512
 -10.500   0.0592   0.08703   0.08079  -0.1469   0.8839   0.0516
 -10.250   0.0601   0.08329   0.07705  -0.1489   0.8805   0.0517
 -10.000   0.0583   0.07883   0.07260  -0.1515   0.8776   0.0517
  -9.500  -0.1510   0.04784   0.04135  -0.1660   0.8591   0.0499
  -9.250  -0.1874   0.04555   0.03887  -0.1627   0.8515   0.0499
  -9.000  -0.2028   0.04356   0.03670  -0.1603   0.8459   0.0501
  -8.750  -0.1961   0.04210   0.03511  -0.1596   0.8428   0.0507
  -8.500  -0.1846   0.04042   0.03324  -0.1597   0.8404   0.0516
  -8.250  -0.1918   0.03963   0.03232  -0.1559   0.8352   0.0522
  -8.000  -0.1938   0.03855   0.03104  -0.1529   0.8295   0.0531
  -7.750  -0.1816   0.03659   0.02870  -0.1525   0.8261   0.0549
  -7.500  -0.1608   0.03493   0.02671  -0.1529   0.8237   0.0567
  -7.250  -0.1341   0.03399   0.02567  -0.1537   0.8220   0.0587
  -7.000  -0.1367   0.03382   0.02539  -0.1494   0.8157   0.0600
  -6.750  -0.1277   0.03311   0.02432  -0.1472   0.8111   0.0627
  -6.500  -0.1052   0.03267   0.02394  -0.1470   0.8084   0.0652
  -6.250  -0.0780   0.03185   0.02287  -0.1475   0.8062   0.0690
  -6.000  -0.0485   0.03119   0.02216  -0.1483   0.8045   0.0724
  -5.750  -0.0171   0.03062   0.02142  -0.1494   0.8031   0.0776
  -5.500  -0.0374   0.03141   0.02223  -0.1420   0.7938   0.0785
  -5.250  -0.0177   0.03137   0.02223  -0.1412   0.7905   0.0819
  -5.000   0.0113   0.03088   0.02156  -0.1416   0.7882   0.0867
  -4.750   0.0450   0.03040   0.02109  -0.1429   0.7864   0.0915
  -4.500   0.0812   0.02972   0.02026  -0.1444   0.7849   0.0973
  -4.250   0.0673   0.03036   0.02093  -0.1380   0.7744   0.0986
  -4.000   0.0922   0.03004   0.02055  -0.1377   0.7711   0.1035
  -3.750   0.1216   0.02963   0.02013  -0.1381   0.7690   0.1092
  -3.500   0.1530   0.02927   0.01972  -0.1388   0.7673   0.1164
  -3.250   0.1859   0.02895   0.01943  -0.1399   0.7659   0.1244
  -3.000   0.1724   0.03005   0.02053  -0.1339   0.7557   0.1276
  -2.750   0.1975   0.02997   0.02043  -0.1337   0.7519   0.1380
  -2.500   0.2298   0.02960   0.02004  -0.1344   0.7495   0.1513
  -2.000   0.3005   0.02873   0.01925  -0.1367   0.7461   0.1841
  -1.750   0.2899   0.02994   0.02046  -0.1314   0.7342   0.1914
  -1.500   0.3180   0.02978   0.02036  -0.1315   0.7312   0.2092
  -1.250   0.3489   0.02955   0.02021  -0.1320   0.7290   0.2290
  -1.000   0.3823   0.02922   0.01991  -0.1328   0.7274   0.2562
  -0.750   0.3792   0.03025   0.02104  -0.1288   0.7165   0.2701
  -0.500   0.4071   0.03000   0.02088  -0.1287   0.7126   0.3054
  -0.250   0.4398   0.02950   0.02055  -0.1293   0.7102   0.3501
   0.000   0.4749   0.02888   0.02016  -0.1303   0.7085   0.4217
   0.250   0.5085   0.02815   0.01994  -0.1307   0.7072   0.5503
   0.750   0.5182   0.02929   0.02156  -0.1228   0.6908   0.7211
   1.000   0.5489   0.02893   0.02115  -0.1223   0.6891   0.7695
   1.500   0.5706   0.02984   0.02205  -0.1169   0.6727   0.8213
   1.750   0.5998   0.02933   0.02150  -0.1161   0.6706   0.8488
   2.250   0.6233   0.03004   0.02224  -0.1112   0.6548   0.8993
   2.500   0.6612   0.02930   0.02152  -0.1123   0.6526   0.9460
   2.750   0.6974   0.02858   0.02072  -0.1131   0.6508   1.0000
   3.250   0.7347   0.02962   0.02165  -0.1117   0.6344   1.0000
   3.500   0.7513   0.03027   0.02225  -0.1107   0.6253   1.0000
   3.750   0.7753   0.03046   0.02239  -0.1104   0.6185   1.0000
   4.000   0.8099   0.02993   0.02179  -0.1110   0.6152   1.0000
   4.250   0.8482   0.02917   0.02097  -0.1120   0.6128   1.0000
   4.500   0.8520   0.03060   0.02239  -0.1098   0.5989   1.0000
   4.750   0.8878   0.02996   0.02169  -0.1105   0.5954   1.0000
   5.250   0.9317   0.03054   0.02223  -0.1093   0.5793   1.0000
   5.500   0.9696   0.02977   0.02140  -0.1102   0.5756   1.0000
   5.750   0.9813   0.03074   0.02237  -0.1086   0.5637   1.0000
   6.000   1.0151   0.03021   0.02180  -0.1091   0.5577   1.0000
   6.250   1.0372   0.03049   0.02206  -0.1085   0.5483   1.0000
   6.500   1.0630   0.03051   0.02205  -0.1082   0.5391   1.0000
   6.750   1.0914   0.03039   0.02190  -0.1081   0.5307   1.0000
   7.000   1.1160   0.03052   0.02199  -0.1077   0.5208   1.0000
   7.250   1.1511   0.03003   0.02143  -0.1083   0.5134   1.0000
   7.500   1.1674   0.03074   0.02216  -0.1072   0.5025   1.0000
   7.750   1.2062   0.03008   0.02141  -0.1082   0.4952   1.0000
   8.000   1.2125   0.03139   0.02277  -0.1062   0.4822   1.0000
   8.250   1.2377   0.03154   0.02285  -0.1058   0.4720   1.0000
   8.500   1.2537   0.03226   0.02358  -0.1047   0.4606   1.0000
   8.750   1.2749   0.03268   0.02397  -0.1041   0.4505   1.0000
   9.000   1.2933   0.03328   0.02455  -0.1032   0.4401   1.0000
   9.250   1.3116   0.03391   0.02515  -0.1023   0.4301   1.0000
   9.500   1.3256   0.03479   0.02605  -0.1011   0.4191   1.0000
   9.750   1.3401   0.03567   0.02693  -0.0999   0.4089   1.0000
  10.000   1.3554   0.03649   0.02774  -0.0988   0.3989   1.0000
  10.250   1.3695   0.03742   0.02867  -0.0977   0.3894   1.0000
  10.500   1.3841   0.03831   0.02956  -0.0966   0.3800   1.0000
  10.750   1.3987   0.03924   0.03047  -0.0956   0.3710   1.0000
  11.000   1.4082   0.04052   0.03181  -0.0942   0.3613   1.0000
  11.250   1.4246   0.04134   0.03260  -0.0934   0.3533   1.0000
  11.500   1.4308   0.04293   0.03431  -0.0919   0.3442   1.0000
  11.750   1.4463   0.04379   0.03511  -0.0910   0.3362   1.0000
  12.000   1.4518   0.04548   0.03691  -0.0896   0.3273   1.0000
  12.250   1.4639   0.04661   0.03801  -0.0885   0.3192   1.0000
  12.500   1.4730   0.04807   0.03954  -0.0874   0.3115   1.0000
  12.750   1.4796   0.04977   0.04132  -0.0862   0.3032   1.0000
  13.000   1.4938   0.05080   0.04228  -0.0854   0.2962   1.0000
  13.250   1.4948   0.05308   0.04476  -0.0841   0.2881   1.0000
  13.500   1.5027   0.05472   0.04643  -0.0831   0.2809   1.0000
  13.750   1.5101   0.05646   0.04824  -0.0822   0.2741   1.0000
  14.000   1.5140   0.05858   0.05047  -0.0812   0.2668   1.0000
  14.250   1.5243   0.06000   0.05184  -0.0804   0.2602   1.0000
  14.500   1.5267   0.06238   0.05437  -0.0796   0.2535   1.0000
  14.750   1.5291   0.06478   0.05688  -0.0788   0.2464   1.0000
  15.000   1.5394   0.06627   0.05833  -0.0782   0.2402   1.0000
  15.250   1.5366   0.06941   0.06168  -0.0775   0.2335   1.0000
  15.500   1.5365   0.07222   0.06460  -0.0770   0.2266   1.0000
  15.750   1.5427   0.07426   0.06664  -0.0765   0.2208   1.0000
  16.000   1.5388   0.07770   0.07027  -0.0762   0.2143   1.0000
  16.250   1.5404   0.08040   0.07303  -0.0760   0.2082   1.0000
  16.500   1.5447   0.08277   0.07540  -0.0757   0.2024   1.0000
  16.750   1.5377   0.08683   0.07968  -0.0759   0.1960   1.0000
  17.000   1.5370   0.08997   0.08289  -0.0759   0.1900   1.0000
  17.250   1.5385   0.09282   0.08577  -0.0760   0.1844   1.0000
  17.500   1.5288   0.09750   0.09068  -0.0767   0.1784   1.0000
  17.750   1.5264   0.10104   0.09430  -0.0772   0.1729   1.0000
  18.000   1.5268   0.10418   0.09748  -0.0777   0.1679   1.0000
  18.250   1.5173   0.10899   0.10249  -0.0789   0.1625   1.0000
  18.500   1.5156   0.11249   0.10605  -0.0797   0.1574   1.0000
  18.750   1.5200   0.11497   0.10848  -0.0802   0.1525   1.0000
  19.000   1.5056   0.12076   0.11452  -0.0822   0.1473   1.0000
<< Back to FX 76-MP-160 (fx76mp160-il)

Polar data table (+)

Polar graphs


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