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EPPLER 551 AIRFOIL (e551-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 551 AIRFOIL (e551-il)
Reynolds number: 50,000
Max Cl/Cd: 4.87 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e551-il-50000.txt
Download as CSV file: xf-e551-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 551 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3865   0.10912   0.10236  -0.0579   1.0000   0.1278
 -11.500  -0.5224   0.08625   0.07962  -0.0749   1.0000   0.1034
 -11.250  -0.5355   0.08166   0.07509  -0.0751   1.0000   0.1024
 -11.000  -0.5593   0.07737   0.07084  -0.0751   1.0000   0.1014
 -10.750  -0.5877   0.07388   0.06740  -0.0740   1.0000   0.1002
 -10.500  -0.6213   0.07138   0.06494  -0.0713   1.0000   0.0988
 -10.250  -0.6579   0.06988   0.06348  -0.0671   1.0000   0.0973
 -10.000  -0.6982   0.06857   0.06215  -0.0620   1.0000   0.0957
  -9.750  -0.7397   0.06663   0.06003  -0.0574   1.0000   0.0935
  -9.500  -0.7914   0.06542   0.05823  -0.0521   1.0000   0.0904
  -9.250  -0.8017   0.06261   0.05526  -0.0495   1.0000   0.0907
  -9.000  -0.8057   0.05959   0.05210  -0.0474   1.0000   0.0914
  -8.750  -0.8021   0.05701   0.04949  -0.0456   1.0000   0.0929
  -8.500  -0.7998   0.05464   0.04698  -0.0436   1.0000   0.0947
  -8.250  -0.7966   0.05223   0.04432  -0.0418   1.0000   0.0959
  -8.000  -0.7903   0.04983   0.04162  -0.0400   1.0000   0.0977
  -7.750  -0.7818   0.04765   0.03909  -0.0383   1.0000   0.1004
  -7.500  -0.7725   0.04580   0.03673  -0.0366   1.0000   0.1036
  -7.250  -0.7565   0.04377   0.03497  -0.0350   1.0000   0.1106
  -7.000  -0.7423   0.04228   0.03315  -0.0333   1.0000   0.1173
  -6.750  -0.7268   0.04079   0.03193  -0.0312   1.0000   0.1283
  -6.500  -0.7135   0.03951   0.03081  -0.0288   1.0000   0.1417
  -6.250  -0.7026   0.03813   0.02951  -0.0264   1.0000   0.1610
  -6.000  -0.6956   0.03627   0.02806  -0.0243   1.0000   0.1896
  -5.750  -0.6918   0.03300   0.02581  -0.0233   1.0000   0.2584
  -5.500  -0.6777   0.03970   0.03402  -0.0137   0.9945   0.4940
  -5.250  -0.6472   0.04758   0.04183  -0.0035   0.9853   0.5370
  -5.000  -0.6138   0.05297   0.04699   0.0037   0.9769   0.5724
  -4.750  -0.5725   0.05705   0.05078   0.0082   0.9688   0.6089
  -4.500  -0.1911   0.06658   0.05883  -0.0142   0.9622   0.8478
  -4.250  -0.4803   0.06146   0.05458   0.0119   0.9532   0.6763
  -4.000  -0.4700   0.06104   0.05402   0.0137   0.9467   0.6968
  -3.750  -0.3938   0.06192   0.05448   0.0084   0.9387   0.7259
  -3.500  -0.3712   0.06133   0.05373   0.0080   0.9318   0.7397
  -3.250  -0.3922   0.06009   0.05244   0.0120   0.9268   0.7451
  -3.000  -0.3639   0.05966   0.05182   0.0108   0.9207   0.7552
  -2.750  -0.3829   0.05844   0.05056   0.0150   0.9165   0.7592
  -2.500  -0.3937   0.05722   0.04927   0.0178   0.9129   0.7638
  -2.250  -0.3648   0.05697   0.04884   0.0160   0.9074   0.7704
  -2.000  -0.3765   0.05588   0.04770   0.0192   0.9054   0.7742
  -1.750  -0.3852   0.05474   0.04649   0.0215   0.9042   0.7778
  -1.500  -0.3802   0.05401   0.04566   0.0226   0.9027   0.7818
  -1.250  -0.3726   0.05347   0.04502   0.0232   0.9025   0.7853
  -1.000  -0.3658   0.05294   0.04440   0.0237   0.9035   0.7894
  -0.750  -0.3566   0.05250   0.04385   0.0233   0.9059   0.7931
   0.000  -0.4472   0.04669   0.03814   0.0440   1.0000   0.8010
   0.250  -0.4280   0.04661   0.03795   0.0427   1.0000   0.8051
   0.500  -0.4066   0.04664   0.03784   0.0407   1.0000   0.8090
   0.750  -0.3850   0.04677   0.03785   0.0387   1.0000   0.8131
   1.000  -0.3670   0.04689   0.03790   0.0380   1.0000   0.8173
   1.250  -0.3457   0.04721   0.03812   0.0364   0.9995   0.8218
   1.500  -0.3090   0.04871   0.03948   0.0314   0.9934   0.8268
   1.750  -0.2801   0.04959   0.04029   0.0284   0.9862   0.8316
   2.000  -0.2505   0.05083   0.04144   0.0254   0.9796   0.8374
   2.250  -0.2146   0.05246   0.04298   0.0208   0.9703   0.8437
   2.500  -0.1897   0.05312   0.04360   0.0187   0.9605   0.8487
   2.750  -0.1623   0.05433   0.04476   0.0161   0.9521   0.8553
   3.000  -0.1275   0.05615   0.04653   0.0121   0.9419   0.8632
   3.250  -0.1074   0.05662   0.04699   0.0110   0.9307   0.8704
   3.500  -0.0787   0.05822   0.04856   0.0081   0.9226   0.8789
   3.750  -0.0496   0.05957   0.04992   0.0055   0.9107   0.8882
   4.000  -0.0303   0.06022   0.05060   0.0044   0.8996   0.8979
   4.250   0.0043   0.06255   0.05296   0.0006   0.8914   0.9114
   4.500   0.0299   0.06344   0.05391  -0.0016   0.8780   0.9254
   4.750   0.0561   0.06460   0.05516  -0.0045   0.8661   0.9412
   5.000   0.0973   0.06696   0.05761  -0.0106   0.8557   0.9628
   5.250   0.1406   0.06958   0.06026  -0.0169   0.8423   1.0000
   5.500   0.1578   0.07024   0.06092  -0.0190   0.8289   1.0000
   5.750   0.1822   0.07199   0.06266  -0.0223   0.8174   1.0000
   6.000   0.2260   0.07556   0.06620  -0.0287   0.8076   1.0000
   6.250   0.2514   0.07720   0.06783  -0.0320   0.7936   1.0000
   6.500   0.2705   0.07879   0.06942  -0.0343   0.7805   1.0000
   6.750   0.2953   0.08118   0.07181  -0.0375   0.7692   1.0000
   7.000   0.3402   0.08525   0.07584  -0.0431   0.7581   1.0000
   7.250   0.3547   0.08657   0.07717  -0.0443   0.7436   1.0000
   7.500   0.3680   0.08831   0.07892  -0.0453   0.7303   1.0000
   7.750   0.3860   0.09068   0.08129  -0.0469   0.7182   1.0000
   8.000   0.4197   0.09433   0.08494  -0.0502   0.7076   1.0000
   8.250   0.4416   0.09672   0.08737  -0.0517   0.6929   1.0000
   8.500   0.4470   0.09821   0.08889  -0.0517   0.6793   1.0000
   8.750   0.4586   0.10048   0.09118  -0.0523   0.6665   1.0000
   9.000   0.4775   0.10339   0.09413  -0.0537   0.6552   1.0000
   9.250   0.5097   0.10709   0.09790  -0.0560   0.6422   1.0000
   9.500   0.5223   0.10918   0.10004  -0.0564   0.6274   1.0000
   9.750   0.5241   0.11099   0.10190  -0.0563   0.6141   1.0000
  10.000   0.5336   0.11354   0.10451  -0.0568   0.6014   1.0000
  10.250   0.5514   0.11673   0.10777  -0.0580   0.5903   1.0000
  10.500   0.5776   0.12025   0.11138  -0.0594   0.5765   1.0000
  10.750   0.6006   0.12340   0.11462  -0.0605   0.5610   1.0000
  11.000   0.5896   0.12475   0.11602  -0.0600   0.5490   1.0000
  11.250   0.5969   0.12756   0.11891  -0.0606   0.5369   1.0000
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