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EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 343 AIRFOIL (e343-il)
Reynolds number: 50,000
Max Cl/Cd: 14.52 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e343-il-50000.txt
Download as CSV file: xf-e343-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 343 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3135   0.11061   0.10461  -0.0238   1.0000   0.2227
  -9.000  -0.2878   0.10576   0.09981  -0.0221   1.0000   0.2335
  -8.750  -0.3250   0.10562   0.09989  -0.0244   1.0000   0.2415
  -8.500  -0.3043   0.10137   0.09571  -0.0224   1.0000   0.2583
  -8.250  -0.2906   0.09777   0.09221  -0.0208   1.0000   0.2743
  -8.000  -0.2854   0.09486   0.08942  -0.0195   1.0000   0.2910
  -7.750  -0.2831   0.09231   0.08702  -0.0181   1.0000   0.3086
  -7.500  -0.2913   0.09041   0.08532  -0.0161   1.0000   0.3289
  -7.250  -0.3068   0.08911   0.08429  -0.0133   1.0000   0.3483
  -7.000  -0.2933   0.08673   0.08210  -0.0097   1.0000   0.3722
  -6.750  -0.3871   0.09170   0.08747  -0.0029   0.9964   0.3481
  -6.500  -0.3158   0.08674   0.08248  -0.0043   0.9852   0.4185
  -6.250  -0.2230   0.08208   0.07775  -0.0029   0.9750   0.5431
  -6.000  -0.1352   0.07740   0.07301  -0.0050   0.9624   0.6710
  -5.750  -0.0393   0.06984   0.06534  -0.0161   0.9472   0.7464
  -5.500  -0.0771   0.04834   0.04400  -0.0482   0.8683   0.4488
  -5.250  -0.1300   0.04544   0.04115  -0.0472   0.8521   0.4254
  -5.000  -0.1805   0.04157   0.03710  -0.0488   0.8383   0.3717
  -4.500  -0.2065   0.04861   0.04136  -0.0527   0.8438   0.1662
  -4.250  -0.1849   0.04620   0.03843  -0.0513   0.8293   0.1466
  -4.000  -0.1617   0.04441   0.03598  -0.0496   0.8160   0.1318
  -3.750  -0.1274   0.04155   0.03265  -0.0497   0.8058   0.1228
  -3.500  -0.1043   0.04085   0.03125  -0.0475   0.7928   0.1168
  -3.250  -0.0803   0.03937   0.02954  -0.0466   0.7807   0.1158
  -3.000   0.2982   0.02710   0.01961  -0.0920   0.7673   1.0000
  -2.750   0.3187   0.02739   0.01937  -0.0909   0.7553   1.0000
  -2.500   0.3369   0.02785   0.01951  -0.0901   0.7434   1.0000
  -2.250   0.3562   0.02821   0.01952  -0.0889   0.7335   1.0000
  -2.000   0.3734   0.02876   0.01984  -0.0879   0.7227   1.0000
  -1.750   0.3914   0.02929   0.02013  -0.0868   0.7136   1.0000
  -1.500   0.4086   0.02994   0.02059  -0.0858   0.7044   1.0000
  -1.250   0.4269   0.03054   0.02098  -0.0847   0.6969   1.0000
  -1.000   0.4418   0.03144   0.02176  -0.0837   0.6878   1.0000
  -0.750   0.4626   0.03185   0.02194  -0.0824   0.6814   1.0000
  -0.500   0.4727   0.03326   0.02333  -0.0814   0.6729   1.0000
  -0.250   0.4896   0.03406   0.02398  -0.0802   0.6664   1.0000
   0.000   0.5039   0.03514   0.02496  -0.0789   0.6602   1.0000
   0.250   0.5109   0.03674   0.02653  -0.0774   0.6528   1.0000
   0.500   0.5283   0.03755   0.02722  -0.0761   0.6473   1.0000
   0.750   0.5345   0.03929   0.02892  -0.0744   0.6420   1.0000
   1.000   0.5281   0.04177   0.03143  -0.0719   0.6361   1.0000
   1.250   0.5369   0.04320   0.03278  -0.0700   0.6309   1.0000
   1.500   0.5594   0.04389   0.03333  -0.0690   0.6265   1.0000
   1.750   0.5211   0.04810   0.03764  -0.0640   0.6229   1.0000
   2.000   0.4874   0.05160   0.04116  -0.0589   0.6208   1.0000
   2.250   0.4473   0.05473   0.04429  -0.0524   0.6205   1.0000
   2.500   0.4183   0.05738   0.04692  -0.0472   0.6213   1.0000
   2.750   0.4043   0.05974   0.04924  -0.0438   0.6233   1.0000
   3.000   0.4023   0.06192   0.05136  -0.0417   0.6254   1.0000
   3.250   0.1823   0.06820   0.05815  -0.0265   0.8100   1.0000
   3.500   0.1886   0.06926   0.05910  -0.0246   0.7977   1.0000
   3.750   0.2237   0.07257   0.06227  -0.0271   0.7893   1.0000
   4.000   0.2249   0.07283   0.06244  -0.0243   0.7741   1.0000
   4.250   0.2306   0.07390   0.06344  -0.0224   0.7609   1.0000
   4.500   0.2658   0.07745   0.06686  -0.0247   0.7532   1.0000
   4.750   0.2617   0.07743   0.06678  -0.0214   0.7390   1.0000
   5.000   0.2673   0.07873   0.06801  -0.0196   0.7278   1.0000
   5.250   0.2991   0.08182   0.07102  -0.0213   0.7181   1.0000
   5.500   0.2943   0.08212   0.07127  -0.0182   0.7047   1.0000
   5.750   0.3189   0.08522   0.07430  -0.0191   0.6983   1.0000
   6.000   0.3216   0.08586   0.07490  -0.0170   0.6845   1.0000
   6.250   0.3251   0.08724   0.07624  -0.0153   0.6742   1.0000
   6.500   0.3515   0.09004   0.07900  -0.0161   0.6647   1.0000
   6.750   0.3464   0.09073   0.07966  -0.0136   0.6536   1.0000
   7.000   0.3781   0.09430   0.08320  -0.0151   0.6458   1.0000
   7.250   0.3695   0.09451   0.08339  -0.0123   0.6333   1.0000
   7.500   0.4073   0.09906   0.08792  -0.0145   0.6270   1.0000
   7.750   0.3917   0.09848   0.08733  -0.0112   0.6142   1.0000
   8.000   0.4235   0.10278   0.09163  -0.0128   0.6086   1.0000
   8.250   0.4139   0.10260   0.09144  -0.0102   0.5954   1.0000
   8.500   0.4267   0.10533   0.09417  -0.0102   0.5885   1.0000
   8.750   0.4345   0.10685   0.09569  -0.0094   0.5772   1.0000
   9.000   0.4456   0.10957   0.09843  -0.0093   0.5706   1.0000
   9.250   0.4551   0.11124   0.10012  -0.0088   0.5590   1.0000
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