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EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 50,000
Max Cl/Cd: 15.75 at α=-1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1233-il-50000.txt
Download as CSV file: xf-e1233-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1233 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3769   0.12013   0.11535  -0.0050   1.0000   0.3432
  -7.500  -0.3914   0.08421   0.07954  -0.0494   0.9583   0.1555
  -7.250  -0.5687   0.08370   0.07852  -0.0385   0.9843   0.1406
  -7.000  -0.5921   0.07402   0.06810  -0.0443   0.9726   0.1280
  -6.750  -0.5735   0.06888   0.06257  -0.0479   0.9608   0.1263
  -6.500  -0.5553   0.06415   0.05739  -0.0508   0.9488   0.1261
  -6.250  -0.5361   0.05978   0.05237  -0.0532   0.9367   0.1267
  -6.000  -0.5112   0.05597   0.04797  -0.0552   0.9245   0.1276
  -5.750  -0.4799   0.05350   0.04560  -0.0571   0.9127   0.1334
  -5.500  -0.4443   0.05067   0.04212  -0.0598   0.9018   0.1406
  -5.250  -0.4109   0.04837   0.03970  -0.0615   0.8898   0.1504
  -5.000  -0.3840   0.04656   0.03754  -0.0621   0.8774   0.1622
  -4.750  -0.3469   0.04487   0.03578  -0.0639   0.8668   0.1810
  -4.500  -0.3123   0.04346   0.03434  -0.0651   0.8552   0.2058
  -4.250  -0.2885   0.04250   0.03336  -0.0646   0.8431   0.2311
  -4.000  -0.2414   0.04090   0.03210  -0.0670   0.8345   0.2761
  -3.750  -0.2292   0.04042   0.03182  -0.0648   0.8213   0.3093
  -3.500  -0.2022   0.03916   0.03114  -0.0644   0.8114   0.3808
  -3.250  -0.1933   0.03864   0.03212  -0.0592   0.8011   0.5210
  -3.000  -0.1965   0.04106   0.03495  -0.0492   0.7902   0.6524
  -2.750  -0.1863   0.04343   0.03717  -0.0405   0.7805   0.7244
  -2.500  -0.1904   0.04504   0.03867  -0.0330   0.7694   0.7615
  -2.250  -0.1657   0.04636   0.03974  -0.0275   0.7611   0.8080
  -2.000   0.4796   0.03932   0.03043  -0.1144   0.7594   0.9721
  -1.750   0.5391   0.03838   0.02928  -0.1222   0.7451   0.9926
  -1.500   0.5775   0.03794   0.02867  -0.1258   0.7336   1.0000
  -1.250   0.5974   0.03794   0.02853  -0.1256   0.7237   1.0000
  -1.000   0.5833   0.03946   0.03007  -0.1202   0.7120   1.0000
  -0.750   0.6107   0.03923   0.02968  -0.1210   0.7039   1.0000
  -0.500   0.5773   0.04164   0.03218  -0.1129   0.6922   1.0000
  -0.250   0.6072   0.04134   0.03171  -0.1139   0.6848   1.0000
   0.000   0.5469   0.04496   0.03550  -0.1026   0.6736   1.0000
   0.250   0.5625   0.04532   0.03575  -0.1015   0.6665   1.0000
   0.500   0.4263   0.05179   0.04253  -0.0816   0.6552   1.0000
   0.750   0.4165   0.05323   0.04393  -0.0779   0.6482   1.0000
   1.000   0.4758   0.05186   0.04234  -0.0816   0.6435   1.0000
   1.250   0.3209   0.05944   0.05026  -0.0637   0.6368   1.0000
   1.500   0.2958   0.06140   0.05221  -0.0592   0.6326   1.0000
   1.750   0.3006   0.06228   0.05300  -0.0572   0.6281   1.0000
   2.000   0.3025   0.06337   0.05402  -0.0550   0.6241   1.0000
   2.250   0.2656   0.06565   0.05632  -0.0497   0.6233   1.0000
   2.500   0.2463   0.06742   0.05808  -0.0461   0.6240   1.0000
   2.750   0.2362   0.06899   0.05961  -0.0433   0.6250   1.0000
   3.250   0.0556   0.07721   0.06830  -0.0317   0.7580   1.0000
   3.500   0.0541   0.07706   0.06809  -0.0298   0.7462   1.0000
   3.750   0.0942   0.08069   0.07156  -0.0336   0.7400   1.0000
   4.000   0.0868   0.08020   0.07102  -0.0312   0.7284   1.0000
   4.250   0.1259   0.08367   0.07435  -0.0348   0.7215   1.0000
   4.500   0.1214   0.08382   0.07445  -0.0331   0.7117   1.0000
   4.750   0.1528   0.08656   0.07708  -0.0357   0.7039   1.0000
   5.000   0.1590   0.08788   0.07833  -0.0355   0.6956   1.0000
   5.250   0.1862   0.09022   0.08059  -0.0374   0.6856   1.0000
   5.500   0.2045   0.09280   0.08309  -0.0387   0.6802   1.0000
   5.750   0.2140   0.09384   0.08408  -0.0387   0.6690   1.0000
   6.000   0.2538   0.09807   0.08821  -0.0421   0.6639   1.0000
   6.250   0.2449   0.09792   0.08805  -0.0403   0.6526   1.0000
   6.500   0.2803   0.10150   0.09154  -0.0430   0.6458   1.0000
   6.750   0.2778   0.10237   0.09239  -0.0422   0.6370   1.0000
   7.000   0.3010   0.10489   0.09485  -0.0436   0.6292   1.0000
   7.500   0.3260   0.10897   0.09887  -0.0448   0.6132   1.0000
   7.750   0.3614   0.11300   0.10284  -0.0473   0.6074   1.0000
   8.000   0.3544   0.11359   0.10343  -0.0464   0.5987   1.0000
   8.250   0.3763   0.11623   0.10604  -0.0476   0.5913   1.0000
   8.500   0.4158   0.12152   0.11129  -0.0506   0.5875   1.0000
   8.750   0.3977   0.12046   0.11025  -0.0487   0.5765   1.0000
   9.000   0.4283   0.12418   0.11394  -0.0506   0.5703   1.0000
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