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

EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E838 HYDROFOIL AIRFOIL (e838-il)
Reynolds number: 200,000
Max Cl/Cd: 51.1 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e838-il-200000.txt
Download as CSV file: xf-e838-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E838 HYDROFOIL AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.6509   0.14132   0.13784  -0.0168   1.0000   0.0286
 -16.500  -0.6799   0.12833   0.12483  -0.0237   1.0000   0.0276
 -16.250  -0.7213   0.11415   0.11052  -0.0321   1.0000   0.0261
 -16.000  -0.7675   0.10136   0.09748  -0.0394   1.0000   0.0252
 -15.750  -0.8100   0.09100   0.08682  -0.0446   1.0000   0.0245
 -15.500  -0.8710   0.08039   0.07562  -0.0489   1.0000   0.0231
 -15.250  -0.8891   0.07553   0.07054  -0.0500   1.0000   0.0231
 -15.000  -0.9027   0.07188   0.06668  -0.0505   1.0000   0.0228
 -14.750  -0.9152   0.06816   0.06276  -0.0507   1.0000   0.0228
 -14.500  -0.9291   0.06359   0.05795  -0.0506   1.0000   0.0229
 -14.250  -0.9345   0.06109   0.05527  -0.0501   1.0000   0.0227
 -14.000  -0.9376   0.05614   0.05010  -0.0497   1.0000   0.0234
 -13.750  -0.9383   0.05329   0.04699  -0.0490   1.0000   0.0232
 -13.500  -0.9282   0.05098   0.04470  -0.0488   1.0000   0.0244
 -13.250  -0.9204   0.04881   0.04241  -0.0483   1.0000   0.0250
 -13.000  -0.9108   0.04675   0.04021  -0.0477   1.0000   0.0257
 -12.750  -0.8966   0.04464   0.03791  -0.0471   1.0000   0.0262
 -12.500  -0.8794   0.04280   0.03589  -0.0465   1.0000   0.0270
 -12.250  -0.8599   0.04124   0.03416  -0.0460   1.0000   0.0280
 -12.000  -0.8408   0.03989   0.03266  -0.0454   1.0000   0.0289
 -11.750  -0.8151   0.03857   0.03140  -0.0448   1.0000   0.0314
 -11.500  -0.7994   0.03740   0.03024  -0.0443   1.0000   0.0335
 -11.250  -0.7831   0.03629   0.02909  -0.0437   1.0000   0.0357
 -11.000  -0.7667   0.03513   0.02790  -0.0429   1.0000   0.0379
 -10.750  -0.7571   0.03366   0.02651  -0.0420   1.0000   0.0406
 -10.500  -0.7459   0.03242   0.02528  -0.0417   1.0000   0.0442
 -10.250  -0.7315   0.03069   0.02356  -0.0427   0.9696   0.0493
 -10.000  -0.7064   0.02882   0.02161  -0.0459   0.9437   0.0583
  -9.750  -0.6949   0.02680   0.01957  -0.0467   0.9224   0.0708
  -9.500  -0.6963   0.02486   0.01773  -0.0451   0.9049   0.0894
  -9.250  -0.7047   0.02293   0.01599  -0.0421   0.8907   0.1245
  -9.000  -0.7163   0.02109   0.01439  -0.0385   0.8786   0.1691
  -8.750  -0.7315   0.01932   0.01288  -0.0341   0.8676   0.2210
  -8.500  -0.7489   0.01773   0.01156  -0.0289   0.8577   0.2746
  -8.250  -0.7678   0.01655   0.01063  -0.0222   0.8499   0.3288
  -8.000  -0.7837   0.01570   0.01018  -0.0155   0.8416   0.3952
  -7.750  -0.7827   0.01532   0.01005  -0.0109   0.8360   0.4623
  -7.500  -0.7698   0.01531   0.01010  -0.0083   0.8298   0.5052
  -7.250  -0.7524   0.01545   0.01019  -0.0064   0.8247   0.5331
  -7.000  -0.7308   0.01579   0.01045  -0.0049   0.8209   0.5535
  -6.750  -0.7075   0.01627   0.01087  -0.0039   0.8157   0.5718
  -6.500  -0.6825   0.01690   0.01143  -0.0029   0.8109   0.5877
  -6.250  -0.6555   0.01740   0.01184  -0.0023   0.8071   0.5985
  -6.000  -0.6327   0.01770   0.01201  -0.0014   0.8032   0.6091
  -5.750  -0.5973   0.01860   0.01292  -0.0020   0.7989   0.6173
  -5.500  -0.5685   0.01920   0.01345  -0.0016   0.7949   0.6264
  -5.250  -0.5365   0.01988   0.01405  -0.0016   0.7916   0.6335
  -5.000  -0.5116   0.02004   0.01412  -0.0012   0.7877   0.6403
  -4.750  -0.4780   0.02056   0.01461  -0.0019   0.7837   0.6441
  -4.500  -0.4597   0.02029   0.01421  -0.0008   0.7797   0.6519
  -4.250  -0.4308   0.02039   0.01423  -0.0009   0.7766   0.6553
  -4.000  -0.4003   0.02063   0.01443  -0.0013   0.7732   0.6581
  -3.750  -0.3740   0.02067   0.01442  -0.0013   0.7689   0.6622
  -3.500  -0.3573   0.02019   0.01381  -0.0003   0.7651   0.6691
  -3.250  -0.3274   0.02028   0.01386  -0.0006   0.7621   0.6713
  -3.000  -0.2988   0.02035   0.01386  -0.0008   0.7595   0.6741
  -2.750  -0.2751   0.02029   0.01379  -0.0007   0.7547   0.6783
  -2.500  -0.2564   0.01988   0.01327   0.0000   0.7508   0.6841
  -2.250  -0.2277   0.01991   0.01327  -0.0003   0.7479   0.6863
  -2.000  -0.1994   0.01993   0.01325  -0.0004   0.7453   0.6889
  -1.750  -0.1748   0.01994   0.01325  -0.0003   0.7413   0.6926
  -1.500  -0.1562   0.01959   0.01281   0.0002   0.7370   0.6986
  -1.250  -0.1280   0.01962   0.01285   0.0000   0.7339   0.7007
  -1.000  -0.0999   0.01964   0.01284  -0.0001   0.7313   0.7033
  -0.750  -0.0727   0.01963   0.01280  -0.0002   0.7288   0.7064
  -0.500  -0.0514   0.01963   0.01282   0.0000   0.7237   0.7108
  -0.250  -0.0279   0.01952   0.01268   0.0001   0.7201   0.7149
   0.000   0.0000   0.01954   0.01271   0.0000   0.7173   0.7173
   0.250   0.0279   0.01952   0.01267  -0.0001   0.7149   0.7201
   0.500   0.0514   0.01963   0.01282   0.0000   0.7107   0.7237
   0.750   0.0726   0.01963   0.01279   0.0002   0.7064   0.7289
   1.000   0.0999   0.01964   0.01285   0.0001   0.7033   0.7313
   1.250   0.1280   0.01962   0.01285   0.0000   0.7007   0.7340
   1.500   0.1562   0.01960   0.01281  -0.0002   0.6986   0.7371
   1.750   0.1747   0.01994   0.01325   0.0004   0.6927   0.7414
   2.000   0.1994   0.01993   0.01325   0.0004   0.6889   0.7454
   2.250   0.2277   0.01991   0.01328   0.0003   0.6863   0.7479
   2.500   0.2563   0.01989   0.01328   0.0000   0.6842   0.7509
   2.750   0.2750   0.02029   0.01379   0.0007   0.6783   0.7548
   3.000   0.2987   0.02036   0.01387   0.0008   0.6741   0.7595
   3.250   0.3272   0.02029   0.01387   0.0006   0.6714   0.7621
   3.500   0.3572   0.02019   0.01382   0.0004   0.6691   0.7651
   3.750   0.3739   0.02067   0.01443   0.0014   0.6623   0.7690
   4.000   0.4001   0.02064   0.01443   0.0013   0.6581   0.7733
   4.250   0.4306   0.02040   0.01424   0.0009   0.6553   0.7767
   4.500   0.4632   0.02015   0.01404   0.0004   0.6530   0.7797
   4.750   0.4778   0.02056   0.01462   0.0019   0.6441   0.7838
   5.000   0.5114   0.02005   0.01413   0.0012   0.6404   0.7878
   5.250   0.5365   0.01988   0.01405   0.0017   0.6336   0.7917
   5.500   0.5683   0.01922   0.01346   0.0016   0.6265   0.7949
   5.750   0.5973   0.01860   0.01292   0.0020   0.6173   0.7990
   6.000   0.6326   0.01770   0.01200   0.0014   0.6091   0.8033
   6.250   0.6553   0.01741   0.01185   0.0023   0.5986   0.8072
   6.500   0.6824   0.01690   0.01143   0.0029   0.5877   0.8109
   6.750   0.7074   0.01626   0.01087   0.0039   0.5717   0.8158
   7.000   0.7307   0.01577   0.01043   0.0050   0.5532   0.8209
   7.250   0.7523   0.01545   0.01019   0.0064   0.5330   0.8248
   7.500   0.7697   0.01531   0.01010   0.0084   0.5053   0.8299
   7.750   0.7828   0.01532   0.01006   0.0109   0.4630   0.8360
   8.000   0.7832   0.01571   0.01018   0.0155   0.3943   0.8417
   8.250   0.7683   0.01653   0.01063   0.0221   0.3295   0.8499
   8.500   0.7489   0.01772   0.01156   0.0289   0.2746   0.8578
   8.750   0.7324   0.01927   0.01285   0.0340   0.2228   0.8677
   9.000   0.7164   0.02108   0.01438   0.0385   0.1691   0.8788
   9.250   0.7041   0.02296   0.01601   0.0422   0.1234   0.8908
   9.500   0.6967   0.02485   0.01772   0.0450   0.0899   0.9050
   9.750   0.6958   0.02675   0.01953   0.0466   0.0711   0.9224
  10.000   0.7063   0.02887   0.02166   0.0458   0.0581   0.9441
  10.500   0.7463   0.03240   0.02526   0.0416   0.0445   1.0000
  10.750   0.7578   0.03363   0.02648   0.0420   0.0407   1.0000
  11.000   0.7674   0.03511   0.02788   0.0429   0.0379   1.0000
  11.250   0.7838   0.03626   0.02906   0.0436   0.0357   1.0000
  11.500   0.7994   0.03740   0.03025   0.0442   0.0332   1.0000
  11.750   0.8140   0.03860   0.03141   0.0447   0.0310   1.0000
  12.000   0.8404   0.03989   0.03267   0.0453   0.0288   1.0000
  12.250   0.8601   0.04122   0.03414   0.0459   0.0279   1.0000
  12.500   0.8799   0.04278   0.03586   0.0465   0.0270   1.0000
  12.750   0.8980   0.04461   0.03788   0.0470   0.0264   1.0000
  13.000   0.9117   0.04673   0.04019   0.0477   0.0257   1.0000
  13.250   0.9215   0.04869   0.04225   0.0482   0.0247   1.0000
  13.500   0.9284   0.05081   0.04448   0.0487   0.0241   1.0000
  13.750   0.9335   0.05337   0.04722   0.0493   0.0239   1.0000
  14.000   0.9417   0.05656   0.05047   0.0495   0.0230   1.0000
  14.500   0.9217   0.06471   0.05912   0.0505   0.0226   1.0000
  14.750   0.9160   0.06810   0.06270   0.0506   0.0228   1.0000
  15.000   0.9028   0.07207   0.06688   0.0504   0.0228   1.0000
  15.250   0.8895   0.07575   0.07076   0.0498   0.0230   1.0000
  15.500   0.8718   0.08025   0.07549   0.0487   0.0232   1.0000
  15.750   0.8506   0.08583   0.08129   0.0470   0.0233   1.0000
  16.000   0.7615   0.10264   0.09880   0.0387   0.0255   1.0000
  16.250   0.7203   0.11464   0.11101   0.0317   0.0263   1.0000
<< Back to EPPLER E838 HYDROFOIL AIRFOIL (e838-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER E838 HYDROFOIL AIRFOIL (e838-il)