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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 50,000
Max Cl/Cd: 16.34 at α=0°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-50000.txt
Download as CSV file: xf-fx73cl2152-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL2-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.1916   0.13248   0.12625  -0.0254   1.0000   0.1959
  -8.500  -0.2177   0.13500   0.12896  -0.0245   1.0000   0.1979
  -8.250  -0.2191   0.13215   0.12626  -0.0231   1.0000   0.1994
  -8.000  -0.2019   0.12733   0.12152  -0.0209   1.0000   0.2028
  -7.750  -0.2076   0.12635   0.12071  -0.0182   1.0000   0.2062
  -7.500  -0.2294   0.12762   0.12222  -0.0143   1.0000   0.2080
  -7.250  -0.2251   0.12790   0.12258  -0.0213   0.9898   0.2156
  -7.000  -0.1779   0.12098   0.11563  -0.0288   0.9771   0.2221
  -6.750  -0.1466   0.11765   0.11226  -0.0368   0.9594   0.2334
  -6.500  -0.1212   0.11358   0.10819  -0.0443   0.9423   0.2388
  -6.250  -0.0748   0.10783   0.10237  -0.0500   0.9275   0.2489
  -6.000  -0.0980   0.11059   0.10518  -0.0550   0.9004   0.2559
  -5.750  -0.0172   0.09993   0.09441  -0.0607   0.8953   0.2694
  -5.500  -0.0487   0.10291   0.09745  -0.0625   0.8684   0.2760
  -5.250   0.0294   0.09293   0.08735  -0.0679   0.8638   0.2877
  -5.000   0.0069   0.09459   0.08907  -0.0711   0.8446   0.2968
  -4.750   0.0668   0.08698   0.08135  -0.0726   0.8356   0.3075
  -4.500   0.0891   0.08370   0.07802  -0.0770   0.8261   0.3214
  -4.250   0.0971   0.08244   0.07673  -0.0779   0.8106   0.3354
  -4.000   0.1270   0.07836   0.07259  -0.0799   0.8001   0.3444
  -3.750   0.1433   0.07629   0.07047  -0.0847   0.7899   0.3599
  -3.500   0.1630   0.07383   0.06798  -0.0829   0.7783   0.3711
  -3.250   0.2041   0.05832   0.05181  -0.1294   0.7693   0.2163
  -3.000   0.1880   0.05955   0.05319  -0.1214   0.7558   0.2202
  -2.750   0.3273   0.04594   0.03858  -0.1567   0.7517   0.2138
  -2.500   0.3640   0.04376   0.03614  -0.1619   0.7412   0.2220
  -2.250   0.4335   0.04066   0.03264  -0.1711   0.7339   0.2432
  -2.000   0.4773   0.03951   0.03129  -0.1751   0.7263   0.2674
  -1.750   0.5134   0.03890   0.03046  -0.1782   0.7173   0.2986
  -1.500   0.5609   0.03812   0.02965  -0.1803   0.7114   0.3421
  -1.250   0.5590   0.03961   0.03118  -0.1771   0.7018   0.3608
  -1.000   0.5916   0.03969   0.03122  -0.1774   0.6953   0.3995
  -0.750   0.6221   0.03977   0.03133  -0.1764   0.6903   0.4321
  -0.500   0.6023   0.04256   0.03418  -0.1724   0.6811   0.4402
  -0.250   0.6269   0.04287   0.03453  -0.1712   0.6753   0.4661
   0.000   0.6846   0.04191   0.03336  -0.1748   0.6709   0.5033
   0.250   0.6015   0.04842   0.04019  -0.1646   0.6616   0.4848
   0.500   0.6264   0.04915   0.04089  -0.1647   0.6562   0.5084
   0.750   0.7033   0.04710   0.03864  -0.1695   0.6522   0.5524
   1.000   0.5971   0.05691   0.04874  -0.1611   0.6452   0.5246
   1.250   0.5834   0.06083   0.05272  -0.1599   0.6410   0.5328
   1.500   0.6093   0.06218   0.05399  -0.1611   0.6362   0.5594
   1.750   0.6757   0.05988   0.05159  -0.1621   0.6312   0.6057
   2.000   0.6359   0.06629   0.05812  -0.1605   0.6297   0.6037
   2.250   0.6244   0.07044   0.06230  -0.1602   0.6288   0.6170
   2.500   0.6197   0.07381   0.06575  -0.1595   0.6286   0.6337
   2.750   0.6260   0.07671   0.06870  -0.1596   0.6297   0.6591
   3.000   0.6401   0.07923   0.07127  -0.1598   0.6312   0.6947
   3.250   0.4634   0.09355   0.08609  -0.1605   0.7773   0.5927
   3.500   0.4965   0.09613   0.08865  -0.1622   0.7706   0.6331
   3.750   0.5003   0.09734   0.08991  -0.1608   0.7591   0.6596
   4.000   0.5306   0.09962   0.09225  -0.1616   0.7514   0.7147
   4.250   0.5308   0.10049   0.09325  -0.1592   0.7393   0.7541
   4.500   0.5444   0.10117   0.09418  -0.1561   0.7324   0.8524
   4.750   0.5529   0.10228   0.09523  -0.1572   0.7197   1.0000
   5.000   0.6059   0.10689   0.09938  -0.1644   0.7122   1.0000
   5.250   0.6093   0.10860   0.10096  -0.1642   0.6996   1.0000
   5.500   0.6496   0.11252   0.10462  -0.1675   0.6924   1.0000
   5.750   0.6485   0.11397   0.10600  -0.1665   0.6795   1.0000
   6.000   0.6839   0.11771   0.10956  -0.1688   0.6730   1.0000
   6.250   0.6813   0.11936   0.11117  -0.1679   0.6622   1.0000
   6.500   0.7102   0.12257   0.11425  -0.1694   0.6544   1.0000
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