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FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL3-152 (fx73cl3152-il)
Reynolds number: 100,000
Max Cl/Cd: 38.44 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl3152-il-100000.txt
Download as CSV file: xf-fx73cl3152-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL3-152                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0236   0.12402   0.11948  -0.0663   0.9588   0.0883
  -9.250  -0.0068   0.12117   0.11663  -0.0721   0.9515   0.0915
  -9.000  -0.0022   0.11999   0.11547  -0.0801   0.9430   0.0928
  -8.750   0.0482   0.11202   0.10745  -0.0828   0.9409   0.0951
  -8.500   0.0708   0.10853   0.10396  -0.0857   0.9310   0.0983
  -8.250   0.0832   0.10740   0.10281  -0.0961   0.9244   0.1032
  -8.000   0.1122   0.10166   0.09708  -0.0982   0.9157   0.1047
  -7.750   0.1537   0.09637   0.09175  -0.1026   0.9107   0.1078
  -7.500   0.1876   0.09236   0.08769  -0.1097   0.9057   0.1129
  -7.250   0.1650   0.09412   0.08950  -0.1135   0.8811   0.1156
  -7.000   0.2109   0.08681   0.08215  -0.1148   0.8748   0.1176
  -6.750   0.2394   0.08308   0.07839  -0.1162   0.8622   0.1209
  -6.500   0.2523   0.08077   0.07604  -0.1174   0.8446   0.1256
  -6.250   0.2241   0.08236   0.07765  -0.1184   0.8173   0.1290
  -6.000   0.2464   0.07752   0.07277  -0.1169   0.8009   0.1311
  -5.750   0.2728   0.07413   0.06929  -0.1161   0.7822   0.1352
  -5.500   0.2784   0.07248   0.06757  -0.1156   0.7619   0.1397
  -5.250   0.2702   0.07219   0.06720  -0.1237   0.7426   0.1450
  -5.000   0.2903   0.06847   0.06336  -0.1193   0.7267   0.1467
  -4.750   0.3091   0.06606   0.06082  -0.1180   0.7114   0.1503
  -4.500   0.3237   0.06517   0.05974  -0.1321   0.6977   0.1611
  -4.250   0.3376   0.06196   0.05642  -0.1268   0.6863   0.1626
  -4.000   0.3521   0.06007   0.05446  -0.1235   0.6739   0.1659
  -3.750   0.3799   0.05795   0.05213  -0.1348   0.6642   0.1794
  -3.500   0.3900   0.05604   0.05022  -0.1301   0.6537   0.1816
  -3.250   0.4706   0.03704   0.03010  -0.1694   0.6484   0.1162
  -3.000   0.5033   0.03346   0.02609  -0.1738   0.6393   0.1151
  -2.750   0.5386   0.03029   0.02234  -0.1776   0.6316   0.1150
  -2.500   0.5705   0.02829   0.01989  -0.1796   0.6250   0.1173
  -2.250   0.5953   0.02794   0.01958  -0.1793   0.6174   0.1223
  -2.000   0.6282   0.02661   0.01768  -0.1806   0.6112   0.1275
  -1.750   0.6562   0.02593   0.01681  -0.1809   0.6052   0.1337
  -1.500   0.6821   0.02561   0.01632  -0.1806   0.5985   0.1426
  -1.250   0.7105   0.02522   0.01584  -0.1807   0.5930   0.1525
  -1.000   0.7413   0.02499   0.01541  -0.1811   0.5887   0.1672
  -0.750   0.7639   0.02500   0.01549  -0.1803   0.5834   0.1840
  -0.500   0.7889   0.02506   0.01559  -0.1798   0.5781   0.2066
  -0.250   0.8171   0.02510   0.01550  -0.1797   0.5735   0.2371
   0.000   0.8468   0.02526   0.01565  -0.1798   0.5696   0.2674
   0.250   0.8677   0.02564   0.01613  -0.1787   0.5647   0.2949
   0.500   0.8904   0.02599   0.01659  -0.1779   0.5602   0.3215
   0.750   0.9152   0.02628   0.01693  -0.1773   0.5561   0.3491
   1.000   0.9435   0.02652   0.01706  -0.1772   0.5523   0.3791
   1.250   0.9688   0.02690   0.01750  -0.1767   0.5487   0.4058
   1.500   0.9871   0.02746   0.01822  -0.1753   0.5442   0.4317
   1.750   1.0096   0.02795   0.01878  -0.1745   0.5401   0.4616
   2.000   1.0356   0.02831   0.01917  -0.1742   0.5362   0.4964
   2.250   1.0651   0.02861   0.01945  -0.1743   0.5328   0.5370
   2.500   1.0905   0.02917   0.02007  -0.1738   0.5294   0.5796
   2.750   1.1044   0.03006   0.02120  -0.1720   0.5251   0.6214
   3.000   1.1242   0.03068   0.02198  -0.1709   0.5209   0.6767
   3.250   1.1525   0.03074   0.02223  -0.1711   0.5171   0.7685
   3.500   1.1864   0.03086   0.02232  -0.1723   0.5137   1.0000
   3.750   1.2167   0.03167   0.02291  -0.1730   0.5108   1.0000
   4.000   1.2200   0.03344   0.02485  -0.1702   0.5063   1.0000
   4.250   1.2321   0.03483   0.02625  -0.1685   0.5019   1.0000
   4.500   1.2557   0.03559   0.02692  -0.1680   0.4982   1.0000
   4.750   1.2855   0.03607   0.02726  -0.1683   0.4951   1.0000
   5.000   1.3192   0.03660   0.02761  -0.1691   0.4925   1.0000
   5.250   1.2950   0.04002   0.03137  -0.1633   0.4874   1.0000
   5.500   1.2701   0.04363   0.03518  -0.1579   0.4819   1.0000
   5.750   1.2888   0.04468   0.03618  -0.1569   0.4784   1.0000
   6.000   1.3348   0.04418   0.03553  -0.1587   0.4760   1.0000
   6.250   1.3783   0.04404   0.03523  -0.1604   0.4738   1.0000
   6.500   1.0663   0.07423   0.06637  -0.1409   0.4539   1.0000
   6.750   0.8834   0.10220   0.09489  -0.1443   0.4520   1.0000
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