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EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 341 AIRFOIL (e341-il)
Reynolds number: 50,000
Max Cl/Cd: 13.6 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e341-il-50000.txt
Download as CSV file: xf-e341-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 341 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4690   0.13367   0.12743   0.0083   1.0000   0.1979
 -10.500  -0.4435   0.12820   0.12197   0.0101   1.0000   0.2075
 -10.250  -0.4685   0.12702   0.12091   0.0063   1.0000   0.2148
 -10.000  -0.4392   0.12158   0.11549   0.0086   1.0000   0.2275
  -9.750  -0.4353   0.11783   0.11183   0.0081   1.0000   0.2371
  -9.500  -0.4601   0.11636   0.11048   0.0051   1.0000   0.2480
  -9.250  -0.4419   0.11204   0.10621   0.0065   1.0000   0.2635
  -9.000  -0.4307   0.10823   0.10247   0.0072   1.0000   0.2790
  -8.750  -0.4290   0.10504   0.09937   0.0074   1.0000   0.2960
  -8.500  -0.4386   0.10243   0.09689   0.0072   1.0000   0.3140
  -8.250  -0.4043   0.09791   0.09238   0.0100   1.0000   0.3382
  -8.000  -0.4239   0.09620   0.09082   0.0104   1.0000   0.3637
  -7.750  -0.4084   0.09313   0.08783   0.0131   1.0000   0.3966
  -7.500  -0.3697   0.08908   0.08382   0.0161   1.0000   0.4360
  -7.250  -0.3476   0.08635   0.08116   0.0193   1.0000   0.4854
  -7.000  -0.3326   0.08461   0.07951   0.0233   1.0000   0.5451
  -6.000  -0.3169   0.05425   0.05043  -0.0109   0.9555   0.4305
  -5.750  -0.3981   0.04417   0.03984  -0.0218   0.9342   0.3012
  -5.500  -0.3984   0.03654   0.03067  -0.0262   0.9202   0.1610
  -5.250  -0.4540   0.05084   0.04389  -0.0139   0.9429   0.1465
  -5.000  -0.4062   0.04574   0.03800  -0.0173   0.9266   0.1218
  -4.750  -0.3616   0.04249   0.03401  -0.0195   0.9090   0.1141
  -4.500  -0.3203   0.03953   0.03056  -0.0212   0.8915   0.1129
  -4.250  -0.2792   0.03696   0.02752  -0.0225   0.8739   0.1120
  -4.000  -0.2386   0.03479   0.02491  -0.0233   0.8565   0.1129
  -3.750   0.0825   0.02676   0.01968  -0.0548   0.8412   1.0000
  -3.500   0.1019   0.02683   0.01926  -0.0537   0.8197   1.0000
  -3.250   0.1217   0.02693   0.01896  -0.0527   0.8012   1.0000
  -3.000   0.1423   0.02706   0.01875  -0.0519   0.7843   1.0000
  -2.750   0.1638   0.02724   0.01861  -0.0515   0.7688   1.0000
  -2.500   0.1859   0.02746   0.01857  -0.0512   0.7545   1.0000
  -2.250   0.2079   0.02773   0.01859  -0.0508   0.7414   1.0000
  -2.000   0.2291   0.02802   0.01863  -0.0502   0.7298   1.0000
  -1.750   0.2514   0.02836   0.01876  -0.0499   0.7181   1.0000
  -1.500   0.2749   0.02881   0.01905  -0.0501   0.7069   1.0000
  -1.250   0.2960   0.02919   0.01921  -0.0492   0.6979   1.0000
  -1.000   0.3196   0.02975   0.01966  -0.0497   0.6873   1.0000
  -0.750   0.3419   0.03032   0.02008  -0.0495   0.6786   1.0000
  -0.500   0.3644   0.03094   0.02060  -0.0495   0.6698   1.0000
  -0.250   0.3865   0.03165   0.02119  -0.0495   0.6619   1.0000
   0.000   0.4085   0.03241   0.02188  -0.0495   0.6535   1.0000
   0.250   0.4297   0.03317   0.02254  -0.0492   0.6466   1.0000
   0.500   0.4510   0.03428   0.02364  -0.0498   0.6387   1.0000
   0.750   0.4716   0.03488   0.02412  -0.0487   0.6329   1.0000
   1.000   0.4901   0.03650   0.02579  -0.0498   0.6249   1.0000
   1.250   0.5095   0.03747   0.02670  -0.0493   0.6188   1.0000
   1.500   0.5271   0.03877   0.02798  -0.0490   0.6132   1.0000
   1.750   0.5396   0.04079   0.03005  -0.0494   0.6064   1.0000
   2.000   0.5574   0.04181   0.03103  -0.0484   0.6010   1.0000
   2.250   0.5672   0.04391   0.03315  -0.0481   0.5958   1.0000
   2.500   0.5682   0.04672   0.03602  -0.0478   0.5906   1.0000
   2.750   0.5786   0.04842   0.03771  -0.0466   0.5857   1.0000
   3.000   0.5942   0.04974   0.03900  -0.0453   0.5813   1.0000
   3.250   0.5737   0.05386   0.04318  -0.0438   0.5790   1.0000
   3.500   0.5532   0.05743   0.04676  -0.0414   0.5778   1.0000
   3.750   0.5320   0.06067   0.04998  -0.0383   0.5780   1.0000
   4.000   0.5147   0.06344   0.05273  -0.0349   0.5798   1.0000
   4.250   0.5103   0.06598   0.05526  -0.0328   0.5825   1.0000
   5.500   0.3343   0.08034   0.06958  -0.0162   0.7030   1.0000
   5.750   0.3398   0.08188   0.07110  -0.0145   0.6905   1.0000
   6.000   0.3704   0.08527   0.07448  -0.0160   0.6821   1.0000
   6.250   0.3711   0.08613   0.07533  -0.0135   0.6678   1.0000
   6.500   0.3709   0.08732   0.07650  -0.0112   0.6547   1.0000
   6.750   0.3812   0.08947   0.07866  -0.0103   0.6451   1.0000
   7.250   0.3962   0.09289   0.08207  -0.0078   0.6216   1.0000
   7.500   0.4099   0.09542   0.08462  -0.0074   0.6129   1.0000
   7.750   0.4241   0.09750   0.08671  -0.0067   0.6008   1.0000
   8.000   0.4186   0.09867   0.08787  -0.0045   0.5899   1.0000
   8.250   0.4552   0.10311   0.09239  -0.0062   0.5821   1.0000
   8.500   0.4408   0.10304   0.09230  -0.0032   0.5690   1.0000
   8.750   0.4425   0.10498   0.09426  -0.0020   0.5601   1.0000
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