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EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 329 AIRFOIL (e329-il)
Reynolds number: 50,000
Max Cl/Cd: 17.35 at α=0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e329-il-50000.txt
Download as CSV file: xf-e329-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 329 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3432   0.11385   0.10739  -0.0239   1.0000   0.2128
  -9.250  -0.3231   0.10931   0.10287  -0.0224   1.0000   0.2229
  -9.000  -0.3563   0.10896   0.10273  -0.0248   1.0000   0.2303
  -8.750  -0.3383   0.10475   0.09855  -0.0230   1.0000   0.2458
  -8.500  -0.3272   0.10117   0.09504  -0.0216   1.0000   0.2609
  -8.250  -0.3224   0.09814   0.09211  -0.0204   1.0000   0.2765
  -8.000  -0.3236   0.09562   0.08970  -0.0192   1.0000   0.2937
  -7.750  -0.3346   0.09365   0.08789  -0.0177   1.0000   0.3118
  -7.500  -0.3084   0.08986   0.08414  -0.0148   1.0000   0.3398
  -7.250  -0.3004   0.08726   0.08164  -0.0120   1.0000   0.3706
  -7.000  -0.2955   0.08516   0.07966  -0.0085   1.0000   0.4075
  -6.750  -0.3078   0.08424   0.07892  -0.0040   1.0000   0.4441
  -6.500  -0.2521   0.08067   0.07531   0.0003   1.0000   0.5242
  -6.250  -0.2009   0.07760   0.07223   0.0040   1.0000   0.6225
  -5.250  -0.1438   0.06742   0.06258   0.0076   1.0000   0.7264
  -5.000  -0.1944   0.06959   0.06507   0.0164   1.0000   0.7208
  -4.750  -0.2369   0.07127   0.06697   0.0227   1.0000   0.7097
  -4.500  -0.3191   0.06733   0.06318   0.0134   0.9711   0.5803
  -4.250  -0.3886   0.06112   0.05700   0.0025   0.9411   0.5112
  -4.000  -0.3194   0.04856   0.04127  -0.0347   0.9209   0.1603
  -3.750  -0.2763   0.04600   0.03763  -0.0362   0.9068   0.1311
  -3.500  -0.2386   0.04270   0.03414  -0.0382   0.8936   0.1250
  -3.250  -0.1951   0.04116   0.03164  -0.0394   0.8808   0.1153
  -3.000  -0.1363   0.03777   0.02796  -0.0437   0.8715   0.1127
  -2.750   0.2427   0.02627   0.01877  -0.0869   0.8902   1.0000
  -2.500   0.2877   0.02586   0.01779  -0.0903   0.8723   1.0000
  -2.250   0.3232   0.02569   0.01720  -0.0920   0.8546   1.0000
  -2.000   0.3491   0.02582   0.01702  -0.0920   0.8369   1.0000
  -1.750   0.3742   0.02600   0.01693  -0.0918   0.8205   1.0000
  -1.500   0.3973   0.02626   0.01695  -0.0913   0.8052   1.0000
  -1.250   0.4162   0.02671   0.01722  -0.0902   0.7904   1.0000
  -1.000   0.4337   0.02725   0.01760  -0.0890   0.7766   1.0000
  -0.750   0.4513   0.02780   0.01800  -0.0877   0.7636   1.0000
  -0.500   0.4716   0.02824   0.01826  -0.0867   0.7526   1.0000
  -0.250   0.4888   0.02882   0.01873  -0.0853   0.7410   1.0000
   0.000   0.5013   0.02971   0.01955  -0.0836   0.7297   1.0000
   0.250   0.5227   0.03013   0.01981  -0.0825   0.7207   1.0000
   0.500   0.5323   0.03122   0.02087  -0.0805   0.7100   1.0000
   0.750   0.5463   0.03209   0.02168  -0.0789   0.7010   1.0000
   1.000   0.5603   0.03295   0.02247  -0.0772   0.6918   1.0000
   1.250   0.5668   0.03429   0.02379  -0.0750   0.6831   1.0000
   1.500   0.5814   0.03515   0.02459  -0.0733   0.6750   1.0000
   1.750   0.5813   0.03685   0.02630  -0.0704   0.6667   1.0000
   2.000   0.5918   0.03796   0.02737  -0.0684   0.6590   1.0000
   2.250   0.5895   0.03976   0.02917  -0.0652   0.6518   1.0000
   2.500   0.5802   0.04181   0.03123  -0.0614   0.6443   1.0000
   2.750   0.5999   0.04255   0.03192  -0.0601   0.6381   1.0000
   3.000   0.5421   0.04653   0.03595  -0.0517   0.6314   1.0000
   3.250   0.5516   0.04772   0.03710  -0.0496   0.6254   1.0000
   3.500   0.5243   0.05018   0.03954  -0.0438   0.6207   1.0000
   3.750   0.4607   0.05335   0.04268  -0.0345   0.6185   1.0000
   4.000   0.4337   0.05571   0.04499  -0.0297   0.6165   1.0000
   4.250   0.4220   0.05784   0.04708  -0.0268   0.6143   1.0000
   4.500   0.4194   0.05993   0.04912  -0.0251   0.6122   1.0000
   4.750   0.4094   0.06250   0.05167  -0.0235   0.6144   1.0000
   5.000   0.4064   0.06506   0.05420  -0.0227   0.6173   1.0000
   5.250   0.4148   0.06780   0.05694  -0.0232   0.6242   1.0000
   5.500   0.3005   0.07332   0.06259  -0.0206   0.7492   1.0000
   5.750   0.3362   0.07674   0.06596  -0.0232   0.7383   1.0000
   6.000   0.3404   0.07763   0.06684  -0.0218   0.7244   1.0000
   6.250   0.3480   0.07918   0.06836  -0.0210   0.7120   1.0000
   6.500   0.3663   0.08161   0.07078  -0.0215   0.7018   1.0000
   6.750   0.3950   0.08454   0.07372  -0.0231   0.6895   1.0000
   7.000   0.3964   0.08564   0.07481  -0.0217   0.6763   1.0000
   7.250   0.4056   0.08762   0.07680  -0.0214   0.6650   1.0000
   7.500   0.4399   0.09146   0.08065  -0.0236   0.6553   1.0000
   7.750   0.4424   0.09256   0.08177  -0.0224   0.6418   1.0000
   8.000   0.4463   0.09432   0.08354  -0.0217   0.6300   1.0000
   8.250   0.4655   0.09729   0.08654  -0.0225   0.6203   1.0000
   8.500   0.4844   0.09983   0.08914  -0.0231   0.6082   1.0000
   8.750   0.4842   0.10142   0.09075  -0.0222   0.5963   1.0000
   9.000   0.4990   0.10430   0.09367  -0.0227   0.5868   1.0000
   9.250   0.5232   0.10748   0.09690  -0.0237   0.5751   1.0000
   9.500   0.5189   0.10890   0.09835  -0.0228   0.5634   1.0000
   9.750   0.5324   0.11190   0.10140  -0.0233   0.5543   1.0000
  10.000   0.5563   0.11524   0.10485  -0.0242   0.5426   1.0000
  10.250   0.5498   0.11669   0.10633  -0.0235   0.5315   1.0000
  10.500   0.5679   0.12028   0.10998  -0.0244   0.5233   1.0000
  10.750   0.5829   0.12299   0.11277  -0.0248   0.5108   1.0000
  11.000   0.5779   0.12484   0.11466  -0.0246   0.5009   1.0000
  11.250   0.6077   0.12963   0.11957  -0.0260   0.4926   1.0000
  11.500   0.6054   0.13094   0.12093  -0.0257   0.4798   1.0000
  11.750   0.6057   0.13351   0.12354  -0.0260   0.4716   1.0000
  12.000   0.6378   0.13841   0.12858  -0.0272   0.4616   1.0000
  12.250   0.6245   0.13919   0.12937  -0.0271   0.4507   1.0000
  12.500   0.6407   0.14331   0.13358  -0.0280   0.4437   1.0000
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