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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 156.91 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-1000000.txt
Download as CSV file: xf-fx74cl5140-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX74_CL5_140                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000   0.0698   0.13688   0.13385  -0.1025   0.6830   0.0036
 -15.750   0.0754   0.13514   0.13193  -0.1032   0.6468   0.0036
  -9.750   0.1999   0.09452   0.09035  -0.1285   0.5086   0.0047
  -9.250   0.2187   0.08996   0.08580  -0.1303   0.5049   0.0050
  -9.000   0.2281   0.08772   0.08356  -0.1312   0.5031   0.0052
  -7.750   0.2741   0.07702   0.07286  -0.1349   0.4939   0.0055
  -7.500   0.2833   0.07495   0.07081  -0.1356   0.4929   0.0055
  -7.250   0.2919   0.07288   0.06875  -0.1361   0.4919   0.0055
  -7.000   0.3005   0.07084   0.06674  -0.1367   0.4904   0.0055
  -6.750   0.3083   0.06885   0.06476  -0.1370   0.4890   0.0055
  -6.500   0.3151   0.06691   0.06285  -0.1372   0.4878   0.0056
  -6.250   0.3198   0.06512   0.06107  -0.1368   0.4866   0.0056
  -6.000   0.3251   0.06336   0.05934  -0.1370   0.4853   0.0057
  -5.750   0.3353   0.06135   0.05732  -0.1381   0.4841   0.0056
  -5.500   0.3470   0.05920   0.05518  -0.1398   0.4826   0.0056
  -5.250   0.3608   0.05693   0.05291  -0.1422   0.4811   0.0057
  -5.000   0.3779   0.05440   0.05038  -0.1458   0.4798   0.0057
  -4.750   0.3977   0.05174   0.04773  -0.1497   0.4790   0.0057
  -4.500   0.4227   0.04861   0.04460  -0.1553   0.4781   0.0057
  -4.250   0.4510   0.04540   0.04136  -0.1613   0.4772   0.0057
  -4.000   0.4824   0.04212   0.03804  -0.1672   0.4761   0.0057
  -3.750   0.5179   0.03867   0.03452  -0.1735   0.4750   0.0057
  -3.500   0.5550   0.03538   0.03114  -0.1794   0.4738   0.0058
  -3.250   0.5954   0.03197   0.02761  -0.1853   0.4726   0.0058
  -3.000   0.6384   0.02855   0.02402  -0.1911   0.4714   0.0058
  -1.750   0.8546   0.01611   0.01031  -0.2141   0.4643   0.0089
  -1.500   0.8904   0.01513   0.00918  -0.2163   0.4634   0.0097
  -1.250   0.9228   0.01510   0.00889  -0.2168   0.4624   0.0114
  -1.000   0.9606   0.01395   0.00748  -0.2192   0.4613   0.0118
  -0.750   0.9943   0.01300   0.00653  -0.2209   0.4601   0.0127
  -0.500   1.0262   0.01258   0.00602  -0.2219   0.4590   0.0140
  -0.250   1.0545   0.01292   0.00619  -0.2217   0.4578   0.0156
   0.000   1.0900   0.01179   0.00512  -0.2239   0.4567   0.0192
   0.250   1.1228   0.01139   0.00472  -0.2252   0.4554   0.0262
   1.000   1.2172   0.01115   0.00429  -0.2275   0.4501   0.0164
   1.250   1.2490   0.01102   0.00413  -0.2284   0.4491   0.0125
   1.500   1.2799   0.01096   0.00403  -0.2292   0.4480   0.0138
   1.750   1.3093   0.01097   0.00402  -0.2297   0.4469   0.0181
   2.000   1.3379   0.01102   0.00405  -0.2301   0.4457   0.0212
   2.250   1.3834   0.01039   0.00464  -0.2348   0.4443   0.7573
   2.500   1.4097   0.01049   0.00479  -0.2345   0.4430   0.7924
   2.750   1.4372   0.01058   0.00487  -0.2347   0.4416   0.7985
   3.000   1.4645   0.01069   0.00497  -0.2348   0.4403   0.8036
   3.250   1.4918   0.01083   0.00511  -0.2350   0.4388   0.8063
   3.500   1.5191   0.01104   0.00529  -0.2352   0.4370   0.8086
   3.750   1.5466   0.01122   0.00546  -0.2354   0.4355   0.8111
   4.000   1.5740   0.01129   0.00556  -0.2356   0.4347   0.8136
   4.250   1.6013   0.01137   0.00570  -0.2357   0.4337   0.8163
   4.500   1.6285   0.01146   0.00582  -0.2359   0.4324   0.8192
   4.750   1.6556   0.01155   0.00594  -0.2361   0.4310   0.8221
   5.000   1.6826   0.01165   0.00607  -0.2362   0.4294   0.8250
   5.250   1.7095   0.01175   0.00620  -0.2364   0.4280   0.8283
   5.500   1.7361   0.01186   0.00636  -0.2365   0.4265   0.8321
   5.750   1.7626   0.01200   0.00653  -0.2366   0.4249   0.8366
   6.000   1.7889   0.01219   0.00674  -0.2367   0.4229   0.8416
   6.250   1.8153   0.01241   0.00701  -0.2368   0.4209   0.8481
   6.500   1.8415   0.01244   0.00714  -0.2368   0.4195   0.8572
   6.750   1.8673   0.01242   0.00723  -0.2368   0.4168   0.8735
   7.000   1.8859   0.01232   0.00730  -0.2351   0.4144   1.0000
   7.250   1.9117   0.01241   0.00743  -0.2351   0.4116   1.0000
   7.500   1.9362   0.01255   0.00756  -0.2349   0.4062   1.0000
   7.750   1.9625   0.01254   0.00764  -0.2350   0.4009   1.0000
   8.000   1.9864   0.01270   0.00778  -0.2346   0.3938   1.0000
   8.250   2.0116   0.01282   0.00796  -0.2346   0.3858   1.0000
   8.500   2.0338   0.01311   0.00822  -0.2339   0.3718   1.0000
   8.750   2.0481   0.01398   0.00886  -0.2320   0.3330   1.0000
   9.000   2.0374   0.01649   0.01081  -0.2258   0.2555   1.0000
   9.250   2.0095   0.01933   0.01322  -0.2166   0.1901   1.0000
   9.500   1.9783   0.02248   0.01607  -0.2075   0.1381   1.0000
   9.750   1.9485   0.02591   0.01932  -0.1999   0.0967   1.0000
  10.000   1.9191   0.02990   0.02321  -0.1937   0.0650   1.0000
  10.250   1.8901   0.03468   0.02795  -0.1891   0.0393   1.0000
  10.500   1.8654   0.03997   0.03326  -0.1864   0.0214   1.0000
  10.750   1.8473   0.04523   0.03860  -0.1850   0.0138   1.0000
  11.000   1.8348   0.05021   0.04369  -0.1843   0.0110   1.0000
  11.250   1.8244   0.05509   0.04870  -0.1839   0.0095   1.0000
  11.500   1.8132   0.06017   0.05389  -0.1835   0.0087   1.0000
  11.750   1.7979   0.06588   0.05972  -0.1832   0.0076   1.0000
  12.000   1.7839   0.07149   0.06546  -0.1830   0.0068   1.0000
  12.250   1.7773   0.07606   0.07012  -0.1830   0.0062   1.0000
  12.500   1.7684   0.08107   0.07524  -0.1830   0.0058   1.0000
  12.750   1.7594   0.08615   0.08040  -0.1831   0.0053   1.0000
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