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FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX74_CL5_140 (fx74cl5140-il)
Reynolds number: 500,000
Max Cl/Cd: 115.53 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74cl5140-il-500000-n5.txt
Download as CSV file: xf-fx74cl5140-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2873   0.09741   0.09211  -0.1393   0.4967   0.0090
  -9.750   0.2964   0.09528   0.08999  -0.1401   0.4956   0.0090
  -9.500   0.3044   0.09311   0.08784  -0.1410   0.4947   0.0090
  -9.250   0.3138   0.09102   0.08576  -0.1418   0.4935   0.0090
  -9.000   0.3220   0.08889   0.08365  -0.1426   0.4924   0.0090
  -8.750   0.3308   0.08685   0.08162  -0.1433   0.4911   0.0090
  -8.500   0.3419   0.08434   0.07912  -0.1434   0.4899   0.0091
  -8.250   0.3522   0.08215   0.07694  -0.1435   0.4886   0.0092
  -8.000   0.3612   0.08018   0.07497  -0.1439   0.4874   0.0092
  -7.750   0.3700   0.07827   0.07307  -0.1444   0.4862   0.0093
  -7.500   0.3786   0.07640   0.07122  -0.1447   0.4850   0.0093
  -7.250   0.3867   0.07452   0.06934  -0.1450   0.4840   0.0094
  -7.000   0.3947   0.07273   0.06756  -0.1452   0.4828   0.0095
  -6.750   0.4020   0.07092   0.06575  -0.1453   0.4816   0.0097
  -6.500   0.4088   0.06921   0.06405  -0.1452   0.4803   0.0098
  -6.250   0.4146   0.06747   0.06234  -0.1449   0.4793   0.0101
  -6.000   0.4189   0.06577   0.06068  -0.1444   0.4784   0.0105
  -5.750   0.4216   0.06427   0.05921  -0.1435   0.4776   0.0107
  -5.500   0.4282   0.06244   0.05742  -0.1439   0.4767   0.0111
  -5.250   0.4375   0.06039   0.05540  -0.1455   0.4759   0.0113
  -5.000   0.4496   0.05808   0.05311  -0.1484   0.4750   0.0114
  -4.750   0.4667   0.05546   0.05050  -0.1526   0.4740   0.0115
  -4.500   0.4835   0.05291   0.04796  -0.1556   0.4729   0.0116
  -4.250   0.4960   0.05119   0.04625  -0.1555   0.4719   0.0117
  -4.000   0.5154   0.04900   0.04405  -0.1583   0.4709   0.0119
  -3.750   0.5397   0.04650   0.04153  -0.1626   0.4698   0.0120
  -3.500   0.5687   0.04380   0.03879  -0.1680   0.4688   0.0121
  -3.250   0.6024   0.04094   0.03586  -0.1741   0.4677   0.0123
  -3.000   0.6410   0.03798   0.03280  -0.1809   0.4666   0.0126
  -2.750   0.6844   0.03492   0.02961  -0.1882   0.4655   0.0129
  -2.500   0.7326   0.03179   0.02631  -0.1958   0.4643   0.0133
  -2.250   0.7936   0.02783   0.02206  -0.2052   0.4633   0.0141
  -1.750   0.8886   0.02285   0.01665  -0.2168   0.4615   0.0148
  -1.500   0.9312   0.02125   0.01484  -0.2208   0.4605   0.0159
  -1.000   1.0200   0.01816   0.01112  -0.2287   0.4583   0.0217
  -0.250   0.2622   0.01130   0.00626   0.0203   0.4545   0.0369
   0.250   1.1957   0.01500   0.00705  -0.2365   0.4524   0.0159
   0.500   1.2267   0.01486   0.00677  -0.2372   0.4513   0.0145
   0.750   1.2572   0.01477   0.00664  -0.2379   0.4503   0.0141
   1.000   1.2892   0.01463   0.00648  -0.2390   0.4489   0.0138
   1.250   1.3209   0.01457   0.00641  -0.2401   0.4476   0.0136
   1.500   1.3520   0.01449   0.00635  -0.2410   0.4464   0.0135
   1.750   1.3826   0.01446   0.00634  -0.2418   0.4450   0.0135
   2.000   1.4125   0.01447   0.00635  -0.2425   0.4436   0.0136
   2.250   1.4417   0.01452   0.00638  -0.2430   0.4422   0.0140
   2.500   1.4709   0.01459   0.00643  -0.2435   0.4410   0.0150
   2.750   1.4994   0.01468   0.00651  -0.2439   0.4399   0.0182
   3.000   1.5457   0.01420   0.00710  -0.2488   0.4386   0.6739
   3.250   1.5724   0.01436   0.00730  -0.2488   0.4375   0.7210
   3.500   1.5987   0.01451   0.00749  -0.2487   0.4363   0.7484
   3.750   1.6245   0.01466   0.00769  -0.2485   0.4352   0.7868
   4.000   1.6508   0.01484   0.00786  -0.2485   0.4340   0.7925
   4.250   1.6772   0.01506   0.00805  -0.2485   0.4328   0.7955
   4.500   1.7036   0.01528   0.00827  -0.2486   0.4316   0.7990
   4.750   1.7297   0.01543   0.00846  -0.2486   0.4307   0.8028
   5.000   1.7556   0.01558   0.00867  -0.2485   0.4295   0.8070
   5.250   1.7813   0.01574   0.00887  -0.2485   0.4281   0.8115
   5.750   1.8323   0.01609   0.00932  -0.2483   0.4252   0.8227
   6.000   1.8573   0.01626   0.00955  -0.2481   0.4238   0.8306
   6.250   1.8818   0.01643   0.00978  -0.2479   0.4223   0.8417
   6.500   1.9048   0.01658   0.00999  -0.2473   0.4206   0.8606
   6.750   1.9190   0.01661   0.01011  -0.2448   0.4190   1.0000
   7.000   1.9426   0.01687   0.01037  -0.2445   0.4174   1.0000
   7.250   1.9662   0.01712   0.01067  -0.2441   0.4160   1.0000
   7.500   1.9895   0.01736   0.01098  -0.2437   0.4146   1.0000
   7.750   2.0123   0.01760   0.01129  -0.2433   0.4129   1.0000
   8.000   2.0340   0.01786   0.01162  -0.2426   0.4113   1.0000
   8.250   2.0549   0.01812   0.01195  -0.2417   0.4097   1.0000
   8.500   2.0750   0.01840   0.01229  -0.2408   0.4081   1.0000
   8.750   2.0944   0.01870   0.01264  -0.2397   0.4066   1.0000
   9.000   2.1133   0.01902   0.01301  -0.2385   0.4051   1.0000
   9.250   2.1318   0.01937   0.01340  -0.2373   0.4036   1.0000
   9.500   2.1494   0.01974   0.01384  -0.2360   0.4017   1.0000
   9.750   2.1668   0.02011   0.01432  -0.2347   0.3989   1.0000
  10.000   2.1824   0.02051   0.01480  -0.2330   0.3953   1.0000
  10.250   2.1971   0.02097   0.01531  -0.2313   0.3923   1.0000
  10.500   2.2088   0.02155   0.01591  -0.2292   0.3887   1.0000
  10.750   2.2243   0.02208   0.01657  -0.2277   0.3855   1.0000
  11.000   2.2378   0.02270   0.01728  -0.2260   0.3818   1.0000
  11.250   2.2488   0.02345   0.01809  -0.2240   0.3779   1.0000
  11.500   2.2570   0.02438   0.01906  -0.2217   0.3742   1.0000
  11.750   2.2684   0.02522   0.02003  -0.2200   0.3688   1.0000
  12.000   2.2721   0.02650   0.02136  -0.2173   0.3615   1.0000
  12.250   2.2776   0.02780   0.02274  -0.2151   0.3541   1.0000
  12.500   2.2753   0.02969   0.02467  -0.2122   0.3446   1.0000
  12.750   2.2674   0.03221   0.02721  -0.2091   0.3323   1.0000
  13.000   2.2554   0.03535   0.03038  -0.2060   0.3207   1.0000
  13.250   2.2391   0.03922   0.03429  -0.2032   0.3095   1.0000
  13.500   2.2176   0.04402   0.03914  -0.2007   0.2984   1.0000
  13.750   2.1930   0.04959   0.04477  -0.1986   0.2879   1.0000
  14.000   2.1658   0.05589   0.05115  -0.1970   0.2770   1.0000
  14.250   2.1357   0.06286   0.05821  -0.1958   0.2680   1.0000
  14.500   2.1014   0.07068   0.06609  -0.1948   0.2598   1.0000
  14.750   2.0728   0.07793   0.07342  -0.1942   0.2508   1.0000
  15.000   2.0422   0.08561   0.08117  -0.1938   0.2400   1.0000
  15.250   2.0141   0.09313   0.08871  -0.1937   0.2280   1.0000
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