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

NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 50,000
Max Cl/Cd: 34.26 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2411-il-50000.txt
Download as CSV file: xf-naca2411-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2.5411                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4047   0.10684   0.09945  -0.0207   1.0000   0.2867
  -8.750  -0.3821   0.10192   0.09450  -0.0195   1.0000   0.2956
  -8.500  -0.4035   0.10086   0.09361  -0.0193   1.0000   0.3045
  -8.250  -0.3853   0.09684   0.08957  -0.0180   1.0000   0.3164
  -8.000  -0.3799   0.09363   0.08641  -0.0169   1.0000   0.3269
  -7.750  -0.3840   0.09121   0.08408  -0.0155   1.0000   0.3403
  -7.500  -0.4088   0.09063   0.08368  -0.0135   1.0000   0.3520
  -7.250  -0.4048   0.08778   0.08089  -0.0114   1.0000   0.3681
  -7.000  -0.3868   0.08383   0.07693  -0.0100   1.0000   0.3814
  -6.750  -0.3848   0.08093   0.07409  -0.0080   1.0000   0.3936
  -6.500  -0.5108   0.06464   0.05786  -0.0306   1.0000   0.1857
  -6.250  -0.5343   0.05500   0.04752  -0.0348   1.0000   0.1618
  -6.000  -0.5300   0.05087   0.04301  -0.0340   1.0000   0.1604
  -5.750  -0.5229   0.04701   0.03877  -0.0330   1.0000   0.1605
  -5.500  -0.5130   0.04333   0.03459  -0.0320   1.0000   0.1609
  -5.250  -0.4978   0.04111   0.03250  -0.0304   1.0000   0.1656
  -5.000  -0.4834   0.03862   0.02965  -0.0292   1.0000   0.1715
  -4.750  -0.4674   0.03575   0.02603  -0.0282   1.0000   0.1763
  -4.500  -0.4497   0.03415   0.02455  -0.0268   1.0000   0.1854
  -4.250  -0.4310   0.03218   0.02220  -0.0257   1.0000   0.1950
  -4.000  -0.4114   0.03071   0.02040  -0.0245   1.0000   0.2082
  -3.750  -0.3913   0.02943   0.01896  -0.0234   1.0000   0.2228
  -3.500  -0.3713   0.02829   0.01778  -0.0222   1.0000   0.2407
  -3.250  -0.3514   0.02727   0.01682  -0.0210   1.0000   0.2612
  -3.000  -0.3312   0.02638   0.01582  -0.0199   1.0000   0.2878
  -2.750  -0.3107   0.02553   0.01504  -0.0188   1.0000   0.3203
  -2.500  -0.2914   0.02471   0.01445  -0.0174   1.0000   0.3589
  -2.250  -0.2708   0.02395   0.01390  -0.0163   1.0000   0.4128
  -2.000  -0.2512   0.02318   0.01356  -0.0149   1.0000   0.4860
  -1.750  -0.2354   0.02229   0.01342  -0.0122   1.0000   0.5996
  -1.500  -0.1595   0.02120   0.01318  -0.0195   1.0000   1.0000
  -1.250  -0.1448   0.02149   0.01305  -0.0187   1.0000   1.0000
  -1.000  -0.1300   0.02185   0.01311  -0.0178   1.0000   1.0000
  -0.750  -0.1151   0.02229   0.01329  -0.0169   1.0000   1.0000
  -0.500  -0.1000   0.02278   0.01356  -0.0161   1.0000   1.0000
  -0.250  -0.0849   0.02333   0.01390  -0.0154   1.0000   1.0000
   0.000  -0.0698   0.02393   0.01433  -0.0148   1.0000   1.0000
   0.250  -0.0219   0.02520   0.01538  -0.0203   0.9868   1.0000
   0.500   0.0286   0.02648   0.01647  -0.0260   0.9718   1.0000
   0.750   0.0760   0.02760   0.01744  -0.0310   0.9565   1.0000
   1.000   0.1181   0.02855   0.01827  -0.0349   0.9411   1.0000
   1.250   0.1592   0.02944   0.01907  -0.0384   0.9257   1.0000
   1.500   0.1994   0.03029   0.01985  -0.0416   0.9106   1.0000
   1.750   0.2390   0.03108   0.02060  -0.0445   0.8957   1.0000
   2.000   0.2744   0.03180   0.02129  -0.0467   0.8805   1.0000
   2.250   0.3080   0.03251   0.02199  -0.0484   0.8654   1.0000
   2.500   0.3406   0.03320   0.02268  -0.0498   0.8502   1.0000
   2.750   0.3722   0.03389   0.02338  -0.0510   0.8352   1.0000
   3.000   0.4031   0.03457   0.02409  -0.0520   0.8201   1.0000
   3.250   0.4340   0.03524   0.02480  -0.0529   0.8050   1.0000
   3.500   0.4646   0.03588   0.02549  -0.0536   0.7898   1.0000
   3.750   0.4951   0.03650   0.02619  -0.0542   0.7746   1.0000
   4.000   0.5262   0.03707   0.02683  -0.0547   0.7592   1.0000
   4.250   0.5579   0.03756   0.02743  -0.0551   0.7436   1.0000
   4.500   0.5910   0.03794   0.02792  -0.0555   0.7277   1.0000
   4.750   0.6270   0.03809   0.02821  -0.0560   0.7116   1.0000
   5.000   0.6680   0.03792   0.02821  -0.0568   0.6953   1.0000
   5.250   0.7118   0.03742   0.02789  -0.0574   0.6785   1.0000
   5.500   0.7609   0.03637   0.02707  -0.0579   0.6611   1.0000
   5.750   0.7982   0.03578   0.02664  -0.0572   0.6413   1.0000
   6.000   0.8284   0.03540   0.02641  -0.0556   0.6189   1.0000
   6.250   0.8849   0.03323   0.02442  -0.0557   0.5944   1.0000
   6.500   0.9256   0.03184   0.02311  -0.0544   0.5656   1.0000
   6.750   0.9600   0.03078   0.02207  -0.0524   0.5331   1.0000
   7.000   0.9805   0.03048   0.02179  -0.0493   0.4978   1.0000
   7.250   1.0033   0.02997   0.02118  -0.0463   0.4573   1.0000
   7.500   1.0184   0.02989   0.02096  -0.0425   0.4126   1.0000
   7.750   1.0304   0.03008   0.02087  -0.0385   0.3635   1.0000
   8.000   1.0394   0.03085   0.02121  -0.0345   0.3144   1.0000
   8.250   1.0478   0.03226   0.02229  -0.0309   0.2714   1.0000
   8.500   1.0599   0.03403   0.02377  -0.0283   0.2364   1.0000
   8.750   1.0775   0.03599   0.02545  -0.0266   0.2088   1.0000
   9.000   1.0926   0.03815   0.02771  -0.0246   0.1884   1.0000
   9.250   1.1113   0.04047   0.03005  -0.0233   0.1720   1.0000
   9.500   1.1289   0.04296   0.03263  -0.0219   0.1594   1.0000
   9.750   1.1486   0.04571   0.03540  -0.0210   0.1493   1.0000
  10.000   1.1580   0.04835   0.03838  -0.0187   0.1418   1.0000
  10.250   1.1722   0.05151   0.04168  -0.0174   0.1355   1.0000
  10.500   1.1689   0.05483   0.04549  -0.0141   0.1327   1.0000
  10.750   1.1648   0.05815   0.04917  -0.0111   0.1297   1.0000
  11.000   1.1885   0.06140   0.05230  -0.0111   0.1238   1.0000
  11.250   1.1757   0.06516   0.05641  -0.0078   0.1227   1.0000
  11.500   1.1566   0.06887   0.06045  -0.0044   0.1224   1.0000
  11.750   1.1350   0.07268   0.06450  -0.0011   0.1225   1.0000
  12.000   1.1129   0.07696   0.06898   0.0011   0.1228   1.0000
  12.250   1.0907   0.08179   0.07397   0.0022   0.1232   1.0000
  12.500   0.9450   0.09895   0.09151  -0.0071   0.1388   1.0000
  12.750   0.9437   0.10439   0.09697  -0.0081   0.1373   1.0000
<< Back to NACA 2.5411 (naca2411-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2.5411 (naca2411-il)