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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 200,000
Max Cl/Cd: 54.15 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel428-il-200000-n5.txt
Download as CSV file: xf-eiffel428-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 428 (Bleriot)                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3495   0.09146   0.08801  -0.0375   1.0000   0.0237
  -9.500  -0.3518   0.08803   0.08463  -0.0384   1.0000   0.0238
  -9.250  -0.3581   0.08444   0.08112  -0.0393   1.0000   0.0240
  -9.000  -0.3631   0.08106   0.07780  -0.0403   0.9984   0.0240
  -8.750  -0.3557   0.07395   0.07072  -0.0495   0.9715   0.0246
  -8.500  -0.3152   0.07303   0.06971  -0.0529   0.9399   0.0265
  -8.250  -0.2840   0.06732   0.06390  -0.0638   0.9171   0.0286
  -8.000  -0.2566   0.06015   0.05657  -0.0755   0.8937   0.0290
  -7.750  -0.2358   0.05284   0.04903  -0.0849   0.8720   0.0298
  -7.500  -0.2234   0.04237   0.03806  -0.0933   0.8524   0.0322
  -7.250  -0.2025   0.04133   0.03692  -0.0938   0.8326   0.0330
  -7.000  -0.1842   0.03843   0.03376  -0.0947   0.8166   0.0338
  -6.750  -0.1660   0.03527   0.03028  -0.0953   0.8016   0.0347
  -6.500  -0.1467   0.03262   0.02729  -0.0955   0.7868   0.0366
  -6.250  -0.1276   0.02944   0.02361  -0.0954   0.7746   0.0378
  -6.000  -0.1073   0.02687   0.02058  -0.0948   0.7630   0.0384
  -5.750  -0.0856   0.02484   0.01809  -0.0941   0.7518   0.0391
  -5.500  -0.0618   0.02394   0.01669  -0.0933   0.7393   0.0404
  -5.250  -0.0404   0.02183   0.01426  -0.0927   0.7278   0.0412
  -5.000  -0.0172   0.02052   0.01266  -0.0920   0.7141   0.0416
  -4.750   0.0065   0.01948   0.01137  -0.0913   0.6985   0.0421
  -4.500   0.0308   0.01863   0.01028  -0.0906   0.6831   0.0428
  -4.250   0.0555   0.01788   0.00932  -0.0900   0.6687   0.0435
  -4.000   0.0803   0.01722   0.00845  -0.0893   0.6516   0.0441
  -3.750   0.1052   0.01663   0.00767  -0.0886   0.6327   0.0449
  -3.500   0.1300   0.01620   0.00706  -0.0880   0.6124   0.0463
  -3.250   0.1550   0.01580   0.00648  -0.0873   0.5893   0.0478
  -3.000   0.1799   0.01537   0.00587  -0.0866   0.5670   0.0486
  -2.750   0.2046   0.01496   0.00530  -0.0859   0.5427   0.0491
  -2.500   0.2291   0.01464   0.00483  -0.0852   0.5179   0.0499
  -2.250   0.2532   0.01442   0.00444  -0.0844   0.4894   0.0508
  -2.000   0.2766   0.01433   0.00415  -0.0835   0.4537   0.0515
  -1.750   0.2989   0.01411   0.00374  -0.0825   0.4158   0.0530
  -1.500   0.3220   0.01401   0.00351  -0.0817   0.3824   0.0548
  -1.250   0.3372   0.01488   0.00366  -0.0797   0.2183   0.0567
  -1.000   0.3617   0.01488   0.00358  -0.0791   0.2015   0.0600
  -0.750   0.3869   0.01487   0.00350  -0.0786   0.1883   0.0638
  -0.500   0.4104   0.01498   0.00344  -0.0779   0.1384   0.0678
  -0.250   0.4353   0.01496   0.00338  -0.0774   0.1349   0.0734
   0.000   0.4602   0.01496   0.00337  -0.0768   0.1318   0.0835
   0.250   0.4834   0.01457   0.00345  -0.0762   0.1304   0.2399
   0.750   0.5700   0.01314   0.00379  -0.0834   0.1269   1.0000
   1.000   0.5942   0.01335   0.00395  -0.0827   0.1247   1.0000
   1.250   0.6177   0.01361   0.00416  -0.0820   0.1216   1.0000
   1.500   0.6408   0.01391   0.00441  -0.0811   0.1185   1.0000
   1.750   0.6639   0.01420   0.00466  -0.0803   0.1156   1.0000
   2.000   0.6878   0.01443   0.00488  -0.0797   0.1136   1.0000
   2.250   0.7115   0.01466   0.00511  -0.0790   0.1122   1.0000
   2.500   0.7349   0.01492   0.00537  -0.0782   0.1104   1.0000
   2.750   0.7578   0.01522   0.00568  -0.0774   0.1084   1.0000
   3.000   0.7799   0.01557   0.00603  -0.0765   0.1062   1.0000
   3.250   0.8018   0.01593   0.00639  -0.0756   0.1038   1.0000
   3.500   0.8265   0.01607   0.00656  -0.0751   0.0998   1.0000
   3.750   0.8496   0.01633   0.00682  -0.0744   0.0949   1.0000
   4.000   0.8742   0.01646   0.00699  -0.0738   0.0903   1.0000
   4.250   0.8988   0.01660   0.00726  -0.0733   0.0637   1.0000
   4.500   0.9200   0.01699   0.00742  -0.0723   0.0561   1.0000
   4.750   0.9403   0.01745   0.00793  -0.0711   0.0533   1.0000
   5.000   0.9591   0.01801   0.00854  -0.0697   0.0505   1.0000
   5.250   0.9760   0.01869   0.00928  -0.0681   0.0476   1.0000
   5.500   0.9943   0.01925   0.00990  -0.0666   0.0460   1.0000
   5.750   1.0122   0.01981   0.01057  -0.0651   0.0442   1.0000
   6.000   1.0280   0.02049   0.01132  -0.0633   0.0418   1.0000
   6.250   1.0412   0.02131   0.01221  -0.0612   0.0398   1.0000
   6.500   1.0476   0.02243   0.01339  -0.0580   0.0380   1.0000
   6.750   1.0620   0.02302   0.01406  -0.0560   0.0363   1.0000
   7.000   1.0741   0.02377   0.01489  -0.0538   0.0342   1.0000
   7.250   1.0842   0.02469   0.01589  -0.0514   0.0323   1.0000
   7.500   1.0926   0.02577   0.01700  -0.0490   0.0305   1.0000
   7.750   1.0993   0.02706   0.01832  -0.0466   0.0290   1.0000
   8.000   1.1120   0.02796   0.01932  -0.0449   0.0274   1.0000
   8.250   1.1229   0.02908   0.02052  -0.0432   0.0256   1.0000
   8.500   1.1339   0.03020   0.02170  -0.0416   0.0241   1.0000
   8.750   1.1447   0.03131   0.02285  -0.0402   0.0227   1.0000
   9.000   1.1540   0.03276   0.02433  -0.0387   0.0216   1.0000
   9.250   1.1669   0.03404   0.02573  -0.0373   0.0203   1.0000
   9.500   1.1803   0.03545   0.02723  -0.0360   0.0192   1.0000
   9.750   1.1927   0.03679   0.02867  -0.0348   0.0180   1.0000
  10.000   1.2028   0.03810   0.03008  -0.0336   0.0171   1.0000
  10.250   1.2114   0.03949   0.03155  -0.0326   0.0164   1.0000
  10.500   1.2195   0.04120   0.03331  -0.0316   0.0156   1.0000
  10.750   1.2338   0.04294   0.03525  -0.0304   0.0149   1.0000
  11.000   1.2475   0.04494   0.03744  -0.0292   0.0143   1.0000
  11.250   1.2585   0.04713   0.03983  -0.0280   0.0136   1.0000
  11.500   1.2660   0.04945   0.04236  -0.0269   0.0131   1.0000
  11.750   1.2703   0.05180   0.04489  -0.0259   0.0127   1.0000
  12.000   1.2712   0.05393   0.04716  -0.0251   0.0123   1.0000
  12.250   1.2716   0.05656   0.04996  -0.0244   0.0120   1.0000
  12.500   1.2705   0.05893   0.05245  -0.0240   0.0117   1.0000
  12.750   1.2679   0.06169   0.05533  -0.0238   0.0114   1.0000
  13.000   1.2621   0.06520   0.05898  -0.0237   0.0111   1.0000
  13.250   1.2543   0.06936   0.06343  -0.0236   0.0110   1.0000
  13.500   1.2428   0.07411   0.06847  -0.0239   0.0108   1.0000
  13.750   1.2289   0.07929   0.07391  -0.0246   0.0107   1.0000
  14.000   1.2125   0.08502   0.07990  -0.0260   0.0106   1.0000
  14.250   1.1949   0.09121   0.08633  -0.0280   0.0106   1.0000
  14.500   1.1771   0.09775   0.09309  -0.0305   0.0106   1.0000
  14.750   1.1584   0.10486   0.10041  -0.0338   0.0106   1.0000
  15.000   1.1383   0.11275   0.10849  -0.0378   0.0106   1.0000
  15.250   1.1180   0.12125   0.11717  -0.0426   0.0107   1.0000
  15.500   1.0965   0.13076   0.12685  -0.0483   0.0107   1.0000
  15.750   1.0768   0.14067   0.13690  -0.0544   0.0108   1.0000
  16.000   1.0559   0.15208   0.14843  -0.0615   0.0110   1.0000
  16.250   1.0329   0.16558   0.16200  -0.0693   0.0111   1.0000
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