Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)
Reynolds number: 500,000
Max Cl/Cd: 119.66 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74modsm-il-500000-n5.txt
Download as CSV file: xf-fx74modsm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-Cl5-140 MOD  (smoothed)                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.2458   0.09248   0.08808  -0.1253   0.6000   0.0098
  -8.500   0.2555   0.09013   0.08571  -0.1266   0.5950   0.0099
  -8.250   0.2650   0.08782   0.08337  -0.1277   0.5903   0.0099
  -8.000   0.2746   0.08546   0.08101  -0.1290   0.5862   0.0099
  -7.750   0.2842   0.08310   0.07866  -0.1304   0.5821   0.0099
  -7.500   0.2935   0.08078   0.07633  -0.1317   0.5780   0.0099
  -7.250   0.3042   0.07833   0.07386  -0.1318   0.5740   0.0101
  -7.000   0.3152   0.07632   0.07185  -0.1323   0.5701   0.0103
  -6.750   0.3259   0.07437   0.06990  -0.1331   0.5658   0.0105
  -6.500   0.3361   0.07244   0.06796  -0.1339   0.5617   0.0108
  -6.000   0.3543   0.06867   0.06421  -0.1355   0.5547   0.0125
  -5.750   0.3682   0.06637   0.06191  -0.1387   0.5514   0.0128
  -5.500   0.3833   0.06399   0.05952  -0.1416   0.5479   0.0128
  -5.250   0.3999   0.06150   0.05702  -0.1447   0.5445   0.0128
  -5.000   0.4186   0.05889   0.05440  -0.1483   0.5413   0.0128
  -4.750   0.4401   0.05608   0.05159  -0.1525   0.5379   0.0128
  -4.500   0.4635   0.05320   0.04868  -0.1570   0.5342   0.0128
  -4.250   0.4892   0.05018   0.04564  -0.1620   0.5306   0.0128
  -4.000   0.5151   0.04735   0.04276  -0.1666   0.5273   0.0128
  -3.750   0.5352   0.04546   0.04087  -0.1683   0.5243   0.0123
  -3.500   0.5747   0.04182   0.03717  -0.1768   0.5209   0.0120
  -3.250   0.6304   0.03699   0.03222  -0.1897   0.5171   0.0122
  -3.000   0.6776   0.03394   0.02905  -0.1985   0.5133   0.0142
  -2.750   0.7451   0.02910   0.02396  -0.2121   0.5098   0.0147
  -2.500   0.8302   0.02284   0.01720  -0.2284   0.5064   0.0141
  -2.250   0.8889   0.01954   0.01344  -0.2365   0.5028   0.0148
  -2.000   0.9440   0.01658   0.00986  -0.2430   0.4992   0.0161
  -1.500   1.0178   0.01458   0.00729  -0.2476   0.4926   0.0171
  -1.250   1.0493   0.01418   0.00677  -0.2486   0.4893   0.0177
  -1.000   1.0798   0.01390   0.00638  -0.2493   0.4861   0.0187
  -0.750   1.1098   0.01366   0.00600  -0.2499   0.4828   0.0198
  -0.500   1.1400   0.01341   0.00565  -0.2505   0.4797   0.0203
  -0.250   1.1709   0.01316   0.00535  -0.2513   0.4766   0.0209
   0.000   1.2008   0.01304   0.00521  -0.2520   0.4733   0.0219
   0.250   1.2297   0.01300   0.00514  -0.2524   0.4703   0.0230
   0.500   1.2578   0.01302   0.00511  -0.2526   0.4673   0.0249
   0.750   1.2864   0.01303   0.00507  -0.2530   0.4645   0.0268
   1.000   1.3150   0.01302   0.00507  -0.2533   0.4616   0.0294
   1.250   1.3428   0.01307   0.00508  -0.2535   0.4583   0.0333
   1.500   1.3702   0.01313   0.00512  -0.2535   0.4552   0.0420
   1.750   1.4014   0.01296   0.00531  -0.2548   0.4524   0.2526
   2.000   1.4320   0.01278   0.00567  -0.2560   0.4496   0.5563
   2.250   1.4592   0.01276   0.00590  -0.2560   0.4470   0.6874
   2.500   1.4841   0.01280   0.00610  -0.2555   0.4439   0.7818
   2.750   1.5074   0.01282   0.00623  -0.2547   0.4409   0.8679
   3.000   1.5295   0.01286   0.00629  -0.2536   0.4381   1.0000
   3.250   1.5547   0.01308   0.00645  -0.2533   0.4355   1.0000
   3.500   1.5804   0.01326   0.00662  -0.2531   0.4330   1.0000
   3.750   1.6060   0.01343   0.00678  -0.2529   0.4302   1.0000
   4.000   1.6310   0.01363   0.00695  -0.2526   0.4272   1.0000
   4.250   1.6554   0.01385   0.00715  -0.2522   0.4242   1.0000
   4.500   1.6792   0.01409   0.00736  -0.2516   0.4215   1.0000
   4.750   1.7028   0.01433   0.00758  -0.2511   0.4191   1.0000
   5.000   1.7272   0.01452   0.00779  -0.2507   0.4165   1.0000
   5.250   1.7509   0.01474   0.00803  -0.2502   0.4136   1.0000
   5.500   1.7737   0.01498   0.00827  -0.2495   0.4106   1.0000
   5.750   1.7954   0.01525   0.00853  -0.2486   0.4079   1.0000
   6.000   1.8156   0.01554   0.00882  -0.2474   0.4054   1.0000
   6.250   1.8371   0.01579   0.00911  -0.2465   0.4030   1.0000
   6.500   1.8585   0.01604   0.00939  -0.2456   0.4003   1.0000
   6.750   1.8789   0.01632   0.00970  -0.2445   0.3973   1.0000
   7.000   1.8982   0.01663   0.01004  -0.2432   0.3945   1.0000
   7.250   1.9170   0.01698   0.01041  -0.2419   0.3920   1.0000
   7.500   1.9349   0.01737   0.01081  -0.2404   0.3895   1.0000
   7.750   1.9548   0.01767   0.01118  -0.2393   0.3869   1.0000
   8.000   1.9738   0.01801   0.01158  -0.2380   0.3841   1.0000
   8.250   1.9914   0.01841   0.01203  -0.2366   0.3812   1.0000
   8.500   2.0081   0.01885   0.01251  -0.2350   0.3785   1.0000
   8.750   2.0236   0.01936   0.01305  -0.2332   0.3759   1.0000
   9.000   2.0404   0.01982   0.01357  -0.2317   0.3734   1.0000
   9.250   2.0577   0.02027   0.01412  -0.2304   0.3705   1.0000
   9.500   2.0722   0.02083   0.01474  -0.2286   0.3660   1.0000
   9.750   2.0815   0.02165   0.01555  -0.2260   0.3589   1.0000
  10.000   2.0920   0.02245   0.01639  -0.2238   0.3493   1.0000
  10.250   2.1012   0.02338   0.01735  -0.2214   0.3418   1.0000
  10.500   2.1089   0.02444   0.01844  -0.2190   0.3338   1.0000
  10.750   2.1163   0.02559   0.01963  -0.2166   0.3255   1.0000
  11.000   2.1192   0.02711   0.02116  -0.2138   0.3168   1.0000
  11.250   2.1251   0.02850   0.02261  -0.2116   0.3077   1.0000
  11.500   2.1250   0.03044   0.02456  -0.2089   0.2975   1.0000
  11.750   2.1191   0.03299   0.02712  -0.2059   0.2835   1.0000
  12.000   2.1085   0.03614   0.03025  -0.2029   0.2678   1.0000
  12.250   2.0932   0.03996   0.03405  -0.1999   0.2513   1.0000
  12.500   2.0740   0.04440   0.03847  -0.1970   0.2351   1.0000
  12.750   2.0510   0.04944   0.04350  -0.1943   0.2192   1.0000
  13.000   2.0267   0.05484   0.04890  -0.1918   0.2044   1.0000
  13.250   1.9989   0.06084   0.05490  -0.1896   0.1887   1.0000
  13.500   1.9726   0.06679   0.06087  -0.1876   0.1753   1.0000
  13.750   1.9447   0.07315   0.06723  -0.1859   0.1610   1.0000
  14.000   1.9169   0.07962   0.07372  -0.1845   0.1475   1.0000
  14.250   1.8875   0.08643   0.08053  -0.1833   0.1325   1.0000
<< Back to FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)

Polar data table (+)

Polar graphs


<< Back to FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il)