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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 500,000
Max Cl/Cd: 118.76 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-500000.txt
Download as CSV file: xf-fx74cl5140-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1865   0.09706   0.09273  -0.1149   0.5619   0.0065
 -11.250   0.1937   0.09461   0.09024  -0.1156   0.5581   0.0066
 -11.000   0.2009   0.09217   0.08776  -0.1163   0.5546   0.0068
 -10.750   0.2082   0.08958   0.08518  -0.1170   0.5516   0.0070
 -10.500   0.2156   0.08710   0.08269  -0.1177   0.5480   0.0072
 -10.250   0.2228   0.08461   0.08018  -0.1184   0.5451   0.0074
 -10.000   0.2299   0.08211   0.07766  -0.1190   0.5426   0.0075
  -9.750   0.2371   0.07965   0.07516  -0.1197   0.5399   0.0075
  -9.500   0.2444   0.07713   0.07265  -0.1203   0.5374   0.0077
  -9.250   0.2517   0.07461   0.07014  -0.1209   0.5351   0.0077
  -9.000   0.2588   0.07212   0.06765  -0.1215   0.5330   0.0078
  -8.750   0.2660   0.06969   0.06521  -0.1221   0.5308   0.0078
  -8.500   0.2732   0.06729   0.06280  -0.1227   0.5289   0.0079
  -8.250   0.2804   0.06495   0.06044  -0.1232   0.5269   0.0079
  -8.000   0.2875   0.06260   0.05807  -0.1238   0.5251   0.0080
  -7.750   0.2945   0.06026   0.05575  -0.1244   0.5236   0.0081
  -7.500   0.3014   0.05796   0.05347  -0.1250   0.5220   0.0081
  -7.250   0.3083   0.05568   0.05120  -0.1255   0.5205   0.0081
  -7.000   0.3141   0.05352   0.04906  -0.1261   0.5188   0.0082
  -6.750   0.3206   0.05129   0.04683  -0.1265   0.5170   0.0082
  -6.500   0.3245   0.04927   0.04484  -0.1271   0.5155   0.0082
  -6.250   0.3291   0.04721   0.04279  -0.1272   0.5140   0.0083
  -6.000   0.3117   0.06574   0.06108  -0.1338   0.5162   0.0082
  -5.750   0.3226   0.06370   0.05903  -0.1352   0.5146   0.0082
  -5.500   0.3353   0.06151   0.05683  -0.1376   0.5129   0.0082
  -5.250   0.3514   0.05911   0.05441  -0.1409   0.5112   0.0082
  -5.000   0.3714   0.05643   0.05172  -0.1453   0.5098   0.0083
  -4.750   0.3930   0.05364   0.04894  -0.1498   0.5085   0.0083
  -4.500   0.4206   0.05035   0.04563  -0.1562   0.5071   0.0083
  -4.250   0.4502   0.04709   0.04234  -0.1621   0.5056   0.0083
  -4.000   0.4696   0.04408   0.03931  -0.1648   0.5041   0.0085
  -3.750   0.4932   0.04164   0.03684  -0.1679   0.5026   0.0088
  -3.500   0.5267   0.03876   0.03388  -0.1734   0.5011   0.0090
  -3.250   0.5655   0.03568   0.03067  -0.1796   0.4995   0.0094
  -3.000   0.6090   0.03248   0.02729  -0.1862   0.4980   0.0101
  -2.750   0.6583   0.02918   0.02373  -0.1928   0.4963   0.0110
  -2.500   0.7158   0.02512   0.01921  -0.2003   0.4947   0.0118
  -2.250   0.7507   0.02336   0.01739  -0.2038   0.4936   0.0128
  -2.000   0.7948   0.02216   0.01570  -0.2066   0.4922   0.0156
  -1.750   0.8349   0.01958   0.01303  -0.2111   0.4906   0.0178
  -1.500   0.8742   0.01837   0.01149  -0.2138   0.4889   0.0229
  -1.250   0.9081   0.01759   0.01058  -0.2156   0.4872   0.0267
  -1.000   0.9439   0.01667   0.00947  -0.2177   0.4858   0.0341
  -0.750   0.9768   0.01620   0.00888  -0.2193   0.4843   0.0486
   0.250   1.1086   0.01457   0.00678  -0.2229   0.4788   0.0405
   0.500   1.1410   0.01432   0.00649  -0.2237   0.4776   0.0287
   0.750   1.1726   0.01421   0.00633  -0.2244   0.4761   0.0220
   1.000   1.2051   0.01408   0.00618  -0.2255   0.4745   0.0197
   1.250   1.2361   0.01404   0.00608  -0.2262   0.4728   0.0195
   1.500   1.2664   0.01405   0.00600  -0.2269   0.4711   0.0256
   1.750   1.2998   0.01393   0.00610  -0.2284   0.4694   0.1859
   2.000   1.3383   0.01354   0.00675  -0.2313   0.4677   0.7816
   2.250   1.3601   0.01367   0.00700  -0.2298   0.4662   0.8508
   2.500   1.3861   0.01387   0.00721  -0.2296   0.4648   0.8695
   2.750   1.4132   0.01396   0.00733  -0.2297   0.4636   0.8738
   3.000   1.4406   0.01409   0.00747  -0.2299   0.4623   0.8781
   3.250   1.4680   0.01421   0.00763  -0.2301   0.4607   0.8829
   3.500   1.4948   0.01433   0.00777  -0.2302   0.4591   0.8889
   3.750   1.5218   0.01445   0.00791  -0.2303   0.4575   0.8964
   4.000   1.5477   0.01455   0.00804  -0.2302   0.4560   0.9072
   4.250   1.5670   0.01456   0.00809  -0.2286   0.4547   1.0000
   4.500   1.5960   0.01478   0.00832  -0.2292   0.4533   1.0000
   4.750   1.6250   0.01507   0.00858  -0.2299   0.4519   1.0000
   5.000   1.6538   0.01546   0.00896  -0.2306   0.4503   1.0000
   5.250   1.6806   0.01563   0.00921  -0.2308   0.4491   1.0000
   5.500   1.7074   0.01583   0.00949  -0.2310   0.4477   1.0000
   5.750   1.7340   0.01602   0.00975  -0.2312   0.4459   1.0000
   6.000   1.7605   0.01619   0.00997  -0.2313   0.4440   1.0000
   6.250   1.7871   0.01636   0.01019  -0.2315   0.4421   1.0000
   6.500   1.8138   0.01654   0.01040  -0.2317   0.4404   1.0000
   6.750   1.8408   0.01676   0.01065  -0.2319   0.4388   1.0000
   7.000   1.8680   0.01707   0.01098  -0.2323   0.4371   1.0000
   7.250   1.8926   0.01730   0.01130  -0.2321   0.4345   1.0000
   7.500   1.9151   0.01732   0.01145  -0.2314   0.4312   1.0000
   7.750   1.9383   0.01729   0.01149  -0.2309   0.4272   1.0000
   8.000   1.9618   0.01725   0.01145  -0.2303   0.4227   1.0000
   8.250   1.9821   0.01726   0.01160  -0.2292   0.4175   1.0000
   8.500   2.0020   0.01717   0.01161  -0.2280   0.4112   1.0000
   8.750   2.0211   0.01717   0.01169  -0.2266   0.4036   1.0000
   9.000   2.0379   0.01716   0.01174  -0.2248   0.3911   1.0000
   9.250   2.0495   0.01744   0.01200  -0.2221   0.3686   1.0000
   9.500   2.0392   0.01886   0.01312  -0.2157   0.3163   1.0000
   9.750   2.0126   0.02167   0.01554  -0.2073   0.2593   1.0000
  10.000   1.9824   0.02506   0.01867  -0.1994   0.2119   1.0000
  10.250   1.9504   0.02906   0.02250  -0.1925   0.1744   1.0000
  10.500   1.9217   0.03349   0.02687  -0.1875   0.1468   1.0000
  10.750   1.8915   0.03892   0.03229  -0.1840   0.1241   1.0000
  11.000   1.8645   0.04492   0.03832  -0.1820   0.1059   1.0000
  11.250   1.8338   0.05210   0.04555  -0.1809   0.0903   1.0000
  11.500   1.8064   0.05924   0.05276  -0.1803   0.0761   1.0000
  11.750   1.7773   0.06679   0.06037  -0.1799   0.0624   1.0000
  12.000   1.7470   0.07466   0.06827  -0.1797   0.0464   1.0000
  12.250   1.7224   0.08190   0.07554  -0.1798   0.0329   1.0000
  12.500   1.6978   0.08934   0.08298  -0.1801   0.0197   1.0000
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