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FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 73-CL2-152 (fx73cl2152-il)
Reynolds number: 500,000
Max Cl/Cd: 104.15 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73cl2152-il-500000.txt
Download as CSV file: xf-fx73cl2152-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0753   0.09894   0.09655  -0.0761   0.9731   0.0423
  -9.250  -0.0553   0.09637   0.09399  -0.0781   0.9679   0.0427
  -9.000  -0.2880   0.02845   0.02463  -0.1540   0.9414   0.0367
  -8.750  -0.2586   0.02494   0.02086  -0.1591   0.9344   0.0374
  -8.500  -0.2232   0.02335   0.01919  -0.1621   0.9286   0.0379
  -8.250  -0.1935   0.02213   0.01791  -0.1634   0.9193   0.0385
  -7.500  -0.0588   0.01780   0.01293  -0.1762   0.8761   0.0414
  -7.250   0.0483   0.01569   0.01040  -0.1933   0.8176   0.0432
  -7.000   0.0933   0.01559   0.00975  -0.1970   0.7272   0.0443
  -6.750   0.1153   0.01548   0.00928  -0.1960   0.6710   0.0451
  -6.250   0.1665   0.01509   0.00835  -0.1953   0.6021   0.0469
  -6.000   0.1945   0.01455   0.00766  -0.1957   0.5783   0.0482
  -5.750   0.2228   0.01431   0.00732  -0.1959   0.5591   0.0493
  -5.500   0.2519   0.01409   0.00698  -0.1962   0.5437   0.0506
  -5.250   0.2813   0.01390   0.00664  -0.1965   0.5310   0.0519
  -5.000   0.3112   0.01373   0.00636  -0.1969   0.5206   0.0531
  -4.750   0.3429   0.01332   0.00589  -0.1979   0.5115   0.0550
  -4.500   0.3736   0.01313   0.00568  -0.1984   0.5040   0.0571
  -4.250   0.4039   0.01303   0.00546  -0.1988   0.4969   0.0592
  -4.000   0.4363   0.01276   0.00515  -0.1998   0.4908   0.0616
  -3.750   0.4677   0.01259   0.00496  -0.2005   0.4853   0.0645
  -3.500   0.4987   0.01248   0.00478  -0.2010   0.4798   0.0680
  -3.250   0.5304   0.01239   0.00463  -0.2018   0.4744   0.0730
  -3.000   0.5626   0.01222   0.00446  -0.2026   0.4707   0.0795
  -2.750   0.5947   0.01206   0.00433  -0.2035   0.4669   0.0908
  -2.500   0.6276   0.01187   0.00425  -0.2045   0.4631   0.1236
  -2.250   0.6585   0.01184   0.00427  -0.2051   0.4593   0.1620
  -2.000   0.6885   0.01195   0.00435  -0.2054   0.4551   0.1820
  -1.750   0.7181   0.01198   0.00440  -0.2056   0.4522   0.1976
  -1.500   0.7479   0.01199   0.00444  -0.2058   0.4495   0.2119
  -1.250   0.7773   0.01203   0.00449  -0.2059   0.4464   0.2244
  -1.000   0.8061   0.01211   0.00453  -0.2059   0.4432   0.2361
  -0.750   0.8357   0.01217   0.00459  -0.2061   0.4399   0.2492
  -0.500   0.8656   0.01234   0.00471  -0.2064   0.4363   0.2618
   0.000   0.9243   0.01245   0.00489  -0.2066   0.4317   0.2958
   0.250   0.9536   0.01249   0.00498  -0.2068   0.4290   0.3153
   0.500   0.9829   0.01253   0.00507  -0.2069   0.4263   0.3339
   0.750   1.0121   0.01260   0.00516  -0.2071   0.4237   0.3540
   1.000   1.0412   0.01271   0.00528  -0.2072   0.4211   0.3770
   1.250   1.0712   0.01290   0.00547  -0.2075   0.4179   0.4022
   1.500   1.1010   0.01303   0.00566  -0.2078   0.4154   0.4281
   1.750   1.1296   0.01309   0.00579  -0.2078   0.4136   0.4556
   2.000   1.1582   0.01316   0.00594  -0.2078   0.4114   0.4836
   2.250   1.1867   0.01325   0.00610  -0.2078   0.4091   0.5115
   2.750   1.2431   0.01347   0.00642  -0.2077   0.4044   0.5682
   3.000   1.2712   0.01363   0.00661  -0.2076   0.4020   0.5959
   3.250   1.3004   0.01390   0.00687  -0.2078   0.3989   0.6224
   3.500   1.3284   0.01405   0.00710  -0.2077   0.3966   0.6508
   3.750   1.3550   0.01413   0.00727  -0.2073   0.3946   0.6788
   4.000   1.3818   0.01422   0.00746  -0.2069   0.3923   0.7072
   4.250   1.4083   0.01433   0.00765  -0.2065   0.3898   0.7382
   4.500   1.4342   0.01444   0.00783  -0.2060   0.3875   0.7726
   4.750   1.4589   0.01454   0.00801  -0.2052   0.3851   0.8128
   5.000   1.4803   0.01464   0.00820  -0.2037   0.3827   0.8728
   5.250   1.4984   0.01480   0.00839  -0.2015   0.3797   1.0000
   5.500   1.5238   0.01492   0.00855  -0.2010   0.3779   1.0000
   5.750   1.5492   0.01506   0.00872  -0.2004   0.3754   1.0000
   6.000   1.5746   0.01522   0.00890  -0.1999   0.3726   1.0000
   6.250   1.5998   0.01540   0.00908  -0.1993   0.3699   1.0000
   6.500   1.6248   0.01560   0.00927  -0.1987   0.3674   1.0000
   6.750   1.6503   0.01588   0.00952  -0.1983   0.3647   1.0000
   7.000   1.6772   0.01625   0.00986  -0.1982   0.3616   1.0000
   7.250   1.7002   0.01641   0.01009  -0.1972   0.3594   1.0000
   7.500   1.7226   0.01659   0.01032  -0.1961   0.3567   1.0000
   7.750   1.7445   0.01677   0.01053  -0.1949   0.3537   1.0000
   8.000   1.7660   0.01697   0.01075  -0.1937   0.3508   1.0000
   8.250   1.7883   0.01725   0.01101  -0.1927   0.3480   1.0000
   8.500   1.8128   0.01766   0.01139  -0.1921   0.3447   1.0000
   8.750   1.8313   0.01781   0.01164  -0.1903   0.3417   1.0000
   9.000   1.8489   0.01796   0.01185  -0.1884   0.3373   1.0000
   9.250   1.8658   0.01816   0.01205  -0.1863   0.3325   1.0000
   9.500   1.8841   0.01853   0.01239  -0.1847   0.3278   1.0000
   9.750   1.9032   0.01876   0.01272  -0.1831   0.3239   1.0000
  10.000   1.9217   0.01905   0.01306  -0.1815   0.3196   1.0000
  10.250   1.9388   0.01943   0.01343  -0.1797   0.3154   1.0000
  10.500   1.9562   0.01990   0.01391  -0.1780   0.3115   1.0000
  10.750   1.9751   0.02024   0.01434  -0.1766   0.3077   1.0000
  11.000   1.9925   0.02066   0.01482  -0.1749   0.3035   1.0000
  11.250   2.0080   0.02119   0.01535  -0.1730   0.2995   1.0000
  11.500   2.0228   0.02179   0.01597  -0.1711   0.2957   1.0000
  11.750   2.0404   0.02225   0.01653  -0.1696   0.2917   1.0000
  12.000   2.0550   0.02284   0.01717  -0.1676   0.2872   1.0000
  12.250   2.0669   0.02359   0.01793  -0.1654   0.2829   1.0000
  12.500   2.0805   0.02430   0.01871  -0.1635   0.2789   1.0000
  12.750   2.0948   0.02498   0.01947  -0.1617   0.2745   1.0000
  13.000   2.1052   0.02588   0.02040  -0.1595   0.2699   1.0000
  13.250   2.1125   0.02700   0.02154  -0.1570   0.2653   1.0000
  13.500   2.1255   0.02782   0.02247  -0.1553   0.2606   1.0000
  13.750   2.1329   0.02900   0.02369  -0.1530   0.2552   1.0000
  14.000   2.1358   0.03054   0.02525  -0.1504   0.2500   1.0000
  14.250   2.1456   0.03168   0.02650  -0.1487   0.2447   1.0000
  14.500   2.1483   0.03337   0.02824  -0.1464   0.2387   1.0000
  14.750   2.1496   0.03528   0.03021  -0.1443   0.2329   1.0000
  15.000   2.1511   0.03728   0.03229  -0.1424   0.2257   1.0000
  15.250   2.1459   0.04001   0.03506  -0.1404   0.2187   1.0000
  15.500   2.1409   0.04294   0.03805  -0.1388   0.2095   1.0000
  15.750   2.1309   0.04660   0.04177  -0.1374   0.2004   1.0000
  16.000   2.1119   0.05159   0.04680  -0.1364   0.1903   1.0000
  16.250   2.0885   0.05757   0.05283  -0.1360   0.1792   1.0000
  16.500   2.0605   0.06456   0.05989  -0.1363   0.1684   1.0000
  16.750   2.0260   0.07285   0.06826  -0.1373   0.1589   1.0000
  17.000   1.9875   0.08211   0.07758  -0.1390   0.1503   1.0000
  17.250   1.9545   0.09077   0.08631  -0.1409   0.1417   1.0000
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