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

EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 500,000
Max Cl/Cd: 95.45 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e550-il-500000-n5.txt
Download as CSV file: xf-e550-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 550 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.7145   0.11377   0.11070  -0.0347   1.0000   0.0042
 -17.000  -0.7544   0.10090   0.09755  -0.0414   1.0000   0.0040
 -16.750  -0.7754   0.09256   0.08905  -0.0459   1.0000   0.0040
 -16.500  -0.7943   0.08504   0.08136  -0.0499   1.0000   0.0040
 -16.250  -0.8096   0.07860   0.07476  -0.0531   1.0000   0.0040
 -16.000  -0.8218   0.07303   0.06906  -0.0558   1.0000   0.0041
 -15.750  -0.8270   0.06877   0.06471  -0.0577   1.0000   0.0041
 -15.500  -0.8383   0.06392   0.05967  -0.0594   1.0000   0.0040
 -15.250  -0.8424   0.06028   0.05593  -0.0606   1.0000   0.0041
 -15.000  -0.8450   0.05695   0.05250  -0.0616   1.0000   0.0042
 -14.750  -0.8473   0.05381   0.04927  -0.0622   1.0000   0.0042
 -14.500  -0.8492   0.05087   0.04620  -0.0626   1.0000   0.0042
 -14.250  -0.8483   0.04834   0.04358  -0.0628   1.0000   0.0043
 -14.000  -0.8465   0.04603   0.04118  -0.0628   1.0000   0.0044
 -13.750  -0.8442   0.04388   0.03894  -0.0626   1.0000   0.0045
 -13.500  -0.8412   0.04185   0.03682  -0.0623   1.0000   0.0045
 -13.250  -0.8379   0.03992   0.03479  -0.0617   1.0000   0.0046
 -13.000  -0.8341   0.03807   0.03286  -0.0611   1.0000   0.0046
 -12.750  -0.8290   0.03640   0.03111  -0.0603   1.0000   0.0047
 -12.500  -0.8220   0.03495   0.02959  -0.0595   1.0000   0.0047
 -12.250  -0.8170   0.03337   0.02794  -0.0585   1.0000   0.0048
 -12.000  -0.8098   0.03204   0.02654  -0.0574   1.0000   0.0049
 -11.750  -0.7928   0.03044   0.02487  -0.0584   0.9969   0.0050
 -11.500  -0.7635   0.02890   0.02321  -0.0613   0.9442   0.0053
 -11.250  -0.6622   0.02640   0.02045  -0.0798   0.9004   0.0055
 -11.000  -0.6208   0.02518   0.01884  -0.0853   0.8261   0.0055
 -10.750  -0.6119   0.02427   0.01774  -0.0839   0.7897   0.0058
 -10.500  -0.6016   0.02347   0.01679  -0.0825   0.7637   0.0061
 -10.250  -0.5911   0.02266   0.01586  -0.0810   0.7433   0.0063
 -10.000  -0.5796   0.02189   0.01497  -0.0797   0.7258   0.0064
  -9.750  -0.5678   0.02115   0.01412  -0.0783   0.7100   0.0065
  -9.500  -0.5554   0.02044   0.01330  -0.0769   0.6951   0.0069
  -9.250  -0.5428   0.01975   0.01252  -0.0756   0.6820   0.0072
  -9.000  -0.5302   0.01908   0.01176  -0.0742   0.6707   0.0074
  -8.750  -0.5198   0.01834   0.01095  -0.0724   0.6590   0.0080
  -8.500  -0.5082   0.01771   0.01025  -0.0708   0.6489   0.0086
  -8.250  -0.4987   0.01713   0.00960  -0.0686   0.6401   0.0092
  -8.000  -0.4891   0.01667   0.00906  -0.0663   0.6314   0.0098
  -7.750  -0.4749   0.01617   0.00851  -0.0646   0.6236   0.0109
  -7.500  -0.4576   0.01576   0.00803  -0.0633   0.6156   0.0119
  -7.250  -0.4398   0.01534   0.00756  -0.0621   0.6084   0.0135
  -7.000  -0.4202   0.01495   0.00712  -0.0611   0.6009   0.0156
  -6.500  -0.3792   0.01420   0.00633  -0.0594   0.5873   0.0251
  -6.250  -0.3579   0.01383   0.00596  -0.0587   0.5806   0.0334
  -6.000  -0.3357   0.01347   0.00561  -0.0581   0.5752   0.0442
  -5.750  -0.3131   0.01308   0.00527  -0.0576   0.5696   0.0592
  -5.500  -0.2908   0.01267   0.00493  -0.0571   0.5642   0.0833
  -5.250  -0.2686   0.01219   0.00457  -0.0566   0.5596   0.1184
  -5.000  -0.2469   0.01154   0.00415  -0.0562   0.5549   0.1764
  -4.750  -0.2272   0.01058   0.00360  -0.0558   0.5501   0.2780
  -4.500  -0.2087   0.00935   0.00298  -0.0553   0.5456   0.4333
  -4.250  -0.1821   0.00917   0.00297  -0.0553   0.5412   0.4973
  -4.000  -0.1537   0.00917   0.00294  -0.0555   0.5367   0.5181
  -3.750  -0.1252   0.00922   0.00294  -0.0556   0.5327   0.5333
  -3.500  -0.0968   0.00930   0.00296  -0.0557   0.5290   0.5459
  -3.250  -0.0681   0.00940   0.00302  -0.0558   0.5256   0.5582
  -3.000  -0.0392   0.00954   0.00310  -0.0560   0.5221   0.5699
  -2.750  -0.0106   0.00959   0.00313  -0.0561   0.5186   0.5746
  -2.500   0.0180   0.00961   0.00307  -0.0563   0.5151   0.5763
  -2.250   0.0465   0.00963   0.00301  -0.0565   0.5117   0.5778
  -2.000   0.0756   0.00962   0.00296  -0.0568   0.5088   0.5793
  -1.750   0.1045   0.00962   0.00291  -0.0571   0.5058   0.5810
  -1.500   0.1334   0.00964   0.00287  -0.0574   0.5028   0.5825
  -1.250   0.1622   0.00966   0.00283  -0.0576   0.5001   0.5838
  -1.000   0.1909   0.00969   0.00279  -0.0579   0.4975   0.5850
  -0.750   0.2194   0.00971   0.00277  -0.0581   0.4950   0.5862
  -0.500   0.2483   0.00970   0.00277  -0.0584   0.4924   0.5875
  -0.250   0.2770   0.00972   0.00278  -0.0586   0.4896   0.5890
   0.000   0.3057   0.00974   0.00279  -0.0589   0.4869   0.5904
   0.250   0.3343   0.00978   0.00281  -0.0591   0.4845   0.5918
   0.500   0.3628   0.00983   0.00282  -0.0594   0.4823   0.5932
   0.750   0.3912   0.00989   0.00285  -0.0596   0.4799   0.5946
   1.000   0.4200   0.00993   0.00288  -0.0598   0.4777   0.5961
   1.250   0.4487   0.00996   0.00292  -0.0601   0.4752   0.5976
   1.500   0.4774   0.01000   0.00296  -0.0604   0.4730   0.5990
   1.750   0.5060   0.01006   0.00300  -0.0607   0.4707   0.6005
   2.000   0.5344   0.01011   0.00305  -0.0609   0.4682   0.6021
   2.250   0.5624   0.01017   0.00311  -0.0611   0.4659   0.6036
   2.500   0.5905   0.01025   0.00319  -0.0612   0.4637   0.6051
   2.750   0.6189   0.01029   0.00328  -0.0615   0.4615   0.6066
   3.000   0.6473   0.01034   0.00336  -0.0617   0.4591   0.6082
   3.250   0.6756   0.01040   0.00345  -0.0619   0.4565   0.6098
   3.500   0.7036   0.01047   0.00354  -0.0621   0.4538   0.6115
   3.750   0.7315   0.01055   0.00362  -0.0623   0.4509   0.6133
   4.000   0.7590   0.01065   0.00372  -0.0624   0.4481   0.6150
   4.250   0.7871   0.01072   0.00382  -0.0626   0.4452   0.6167
   4.500   0.8150   0.01078   0.00393  -0.0627   0.4417   0.6185
   4.750   0.8425   0.01084   0.00405  -0.0628   0.4382   0.6205
   5.000   0.8697   0.01093   0.00416  -0.0629   0.4347   0.6224
   5.250   0.8966   0.01104   0.00429  -0.0629   0.4313   0.6245
   5.500   0.9242   0.01110   0.00443  -0.0630   0.4275   0.6265
   5.750   0.9513   0.01118   0.00456  -0.0630   0.4229   0.6287
   6.000   0.9778   0.01129   0.00469  -0.0629   0.4184   0.6308
   6.250   1.0044   0.01139   0.00484  -0.0629   0.4138   0.6330
   6.750   1.0569   0.01160   0.00514  -0.0627   0.4025   0.6372
   7.000   1.0829   0.01170   0.00532  -0.0626   0.3965   0.6395
   7.250   1.1084   0.01183   0.00550  -0.0623   0.3891   0.6420
   7.500   1.1333   0.01198   0.00569  -0.0620   0.3812   0.6448
   7.750   1.1570   0.01217   0.00589  -0.0615   0.3708   0.6478
   8.000   1.1807   0.01237   0.00612  -0.0610   0.3584   0.6508
   8.250   1.2019   0.01265   0.00638  -0.0601   0.3424   0.6536
   8.500   1.2209   0.01302   0.00673  -0.0589   0.3232   0.6566
   8.750   1.2377   0.01349   0.00715  -0.0573   0.3014   0.6598
   9.000   1.2508   0.01409   0.00766  -0.0552   0.2783   0.6631
   9.250   1.2615   0.01472   0.00822  -0.0526   0.2560   0.6665
   9.500   1.2681   0.01537   0.00881  -0.0494   0.2368   0.6698
   9.750   1.2744   0.01608   0.00949  -0.0462   0.2195   0.6736
  10.000   1.2798   0.01687   0.01024  -0.0431   0.2023   0.6777
  10.250   1.2838   0.01774   0.01108  -0.0400   0.1864   0.6821
  10.500   1.2856   0.01876   0.01208  -0.0368   0.1709   0.6864
  10.750   1.2868   0.01989   0.01320  -0.0339   0.1581   0.6914
  11.000   1.2865   0.02123   0.01455  -0.0313   0.1457   0.6972
  11.250   1.2867   0.02271   0.01605  -0.0290   0.1350   0.7030
  11.500   1.2876   0.02429   0.01767  -0.0272   0.1253   0.7093
  11.750   1.2871   0.02612   0.01952  -0.0255   0.1165   0.7161
  12.000   1.2851   0.02819   0.02163  -0.0241   0.1075   0.7229
  12.250   1.2856   0.03019   0.02369  -0.0230   0.0998   0.7308
  12.500   1.2832   0.03251   0.02604  -0.0219   0.0923   0.7389
  12.750   1.2810   0.03491   0.02849  -0.0210   0.0845   0.7483
  13.000   1.2796   0.03729   0.03094  -0.0203   0.0782   0.7587
  13.250   1.2772   0.03983   0.03353  -0.0197   0.0722   0.7707
  13.500   1.2756   0.04232   0.03611  -0.0192   0.0663   0.7854
  14.000   1.2720   0.04740   0.04141  -0.0182   0.0566   0.8330
  14.250   1.2739   0.05014   0.04440  -0.0189   0.0516   0.9319
  14.500   1.2742   0.05274   0.04705  -0.0190   0.0478   1.0000
  14.750   1.2732   0.05569   0.05002  -0.0192   0.0440   1.0000
  15.000   1.2748   0.05841   0.05278  -0.0195   0.0405   1.0000
  15.250   1.2745   0.06141   0.05581  -0.0199   0.0374   1.0000
  15.500   1.2757   0.06429   0.05874  -0.0204   0.0346   1.0000
  15.750   1.2760   0.06735   0.06182  -0.0209   0.0317   1.0000
  16.000   1.2766   0.07041   0.06493  -0.0216   0.0293   1.0000
  16.250   1.2776   0.07348   0.06804  -0.0223   0.0269   1.0000
  16.500   1.2774   0.07679   0.07139  -0.0231   0.0249   1.0000
  16.750   1.2793   0.07984   0.07450  -0.0239   0.0230   1.0000
  17.000   1.2780   0.08338   0.07808  -0.0250   0.0211   1.0000
  17.250   1.2792   0.08663   0.08139  -0.0260   0.0195   1.0000
  17.500   1.2784   0.09023   0.08504  -0.0271   0.0178   1.0000
  17.750   1.2787   0.09369   0.08856  -0.0283   0.0166   1.0000
  18.000   1.2784   0.09731   0.09225  -0.0296   0.0154   1.0000
  18.250   1.2767   0.10117   0.09616  -0.0311   0.0141   1.0000
  18.500   1.2766   0.10485   0.09991  -0.0325   0.0132   1.0000
  18.750   1.2757   0.10867   0.10381  -0.0341   0.0123   1.0000
  19.000   1.2747   0.11258   0.10779  -0.0358   0.0116   1.0000
<< Back to EPPLER 550 AIRFOIL (e550-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 550 AIRFOIL (e550-il)