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Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 428 (Bleriot) (eiffel428-il)
Reynolds number: 100,000
Max Cl/Cd: 59.37 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel428-il-100000.txt
Download as CSV file: xf-eiffel428-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3400   0.10262   0.09771  -0.0353   1.0000   0.0788
  -9.500  -0.3562   0.10216   0.09740  -0.0386   1.0000   0.0801
  -9.250  -0.3715   0.10108   0.09647  -0.0404   1.0000   0.0804
  -9.000  -0.3361   0.09336   0.08866  -0.0355   1.0000   0.0847
  -8.750  -0.3337   0.09082   0.08618  -0.0349   1.0000   0.0873
  -8.500  -0.3381   0.08869   0.08415  -0.0344   1.0000   0.0901
  -8.250  -0.3503   0.08708   0.08269  -0.0336   1.0000   0.0922
  -8.000  -0.3687   0.08599   0.08176  -0.0345   1.0000   0.0941
  -7.750  -0.3928   0.08565   0.08155  -0.0330   1.0000   0.0947
  -7.500  -0.4153   0.08530   0.08126  -0.0324   1.0000   0.0951
  -7.250  -0.4195   0.08186   0.07782  -0.0351   0.9983   0.0962
  -7.000  -0.4011   0.07798   0.07403  -0.0302   0.9949   0.0994
  -6.750  -0.3598   0.07201   0.06778  -0.0478   0.9841   0.1116
  -6.500  -0.3417   0.06906   0.06494  -0.0437   0.9788   0.1171
  -6.250  -0.3056   0.06391   0.05963  -0.0537   0.9710   0.1290
  -6.000  -0.2762   0.06000   0.05556  -0.0601   0.9611   0.1427
  -5.750  -0.2450   0.05653   0.05198  -0.0644   0.9537   0.1575
  -5.500  -0.2137   0.05352   0.04895  -0.0667   0.9456   0.1752
  -5.250  -0.1767   0.05032   0.04551  -0.0727   0.9352   0.2020
  -5.000  -0.1326   0.04657   0.04177  -0.0763   0.9288   0.2235
  -4.750  -0.0938   0.04385   0.03885  -0.0804   0.9174   0.2598
  -4.000   0.0458   0.02809   0.02045  -0.0953   0.8903   0.1244
  -3.750   0.0868   0.02515   0.01706  -0.0972   0.8829   0.1152
  -3.500   0.1149   0.02379   0.01526  -0.0966   0.8716   0.1139
  -3.250   0.1474   0.02305   0.01409  -0.0966   0.8630   0.1109
  -3.000   0.1795   0.02162   0.01247  -0.0968   0.8538   0.1101
  -2.750   0.2072   0.02068   0.01136  -0.0962   0.8423   0.1102
  -2.500   0.2365   0.01978   0.01033  -0.0958   0.8321   0.1113
  -2.250   0.2651   0.01876   0.00940  -0.0955   0.8227   0.1173
  -2.000   0.2899   0.01825   0.00889  -0.0946   0.8122   0.1214
  -1.750   0.3175   0.01774   0.00832  -0.0939   0.8040   0.1253
  -1.500   0.3422   0.01724   0.00788  -0.0929   0.7941   0.1320
  -1.250   0.3676   0.01690   0.00757  -0.0921   0.7845   0.1448
  -1.000   0.4389   0.01395   0.00704  -0.1004   0.7768   1.0000
  -0.750   0.4628   0.01410   0.00692  -0.0992   0.7662   1.0000
  -0.500   0.4885   0.01422   0.00680  -0.0984   0.7573   1.0000
  -0.250   0.5135   0.01435   0.00677  -0.0976   0.7479   1.0000
   0.000   0.5376   0.01450   0.00679  -0.0966   0.7375   1.0000
   0.250   0.5637   0.01458   0.00671  -0.0959   0.7282   1.0000
   0.500   0.5877   0.01473   0.00678  -0.0949   0.7178   1.0000
   0.750   0.6122   0.01490   0.00689  -0.0941   0.7085   1.0000
   1.000   0.6382   0.01502   0.00692  -0.0935   0.7002   1.0000
   1.250   0.6617   0.01523   0.00711  -0.0926   0.6905   1.0000
   1.500   0.6887   0.01535   0.00716  -0.0922   0.6836   1.0000
   1.750   0.7116   0.01553   0.00737  -0.0911   0.6726   1.0000
   2.000   0.7355   0.01561   0.00742  -0.0901   0.6604   1.0000
   2.250   0.7596   0.01562   0.00740  -0.0890   0.6472   1.0000
   2.500   0.7833   0.01561   0.00737  -0.0878   0.6329   1.0000
   2.750   0.8065   0.01560   0.00736  -0.0866   0.6170   1.0000
   3.000   0.8302   0.01565   0.00742  -0.0855   0.6037   1.0000
   3.250   0.8546   0.01574   0.00751  -0.0847   0.5922   1.0000
   3.500   0.8778   0.01583   0.00764  -0.0836   0.5781   1.0000
   3.750   0.8999   0.01591   0.00778  -0.0823   0.5597   1.0000
   4.000   0.9217   0.01600   0.00789  -0.0810   0.5384   1.0000
   4.250   0.9437   0.01613   0.00800  -0.0797   0.5181   1.0000
   4.500   0.9651   0.01633   0.00825  -0.0783   0.4951   1.0000
   4.750   0.9849   0.01659   0.00842  -0.0767   0.4630   1.0000
   5.000   1.0036   0.01697   0.00868  -0.0749   0.4256   1.0000
   5.250   1.0224   0.01742   0.00908  -0.0732   0.3865   1.0000
   5.500   1.0258   0.01883   0.00969  -0.0693   0.2592   1.0000
   5.750   1.0332   0.02030   0.01078  -0.0663   0.1987   1.0000
   6.000   1.0384   0.02191   0.01190  -0.0632   0.1344   1.0000
   6.250   1.0465   0.02324   0.01316  -0.0603   0.1201   1.0000
   6.500   1.0527   0.02461   0.01459  -0.0572   0.1070   1.0000
   6.750   1.0621   0.02572   0.01580  -0.0544   0.0943   1.0000
   7.000   1.0738   0.02658   0.01680  -0.0518   0.0837   1.0000
   7.250   1.0845   0.02749   0.01780  -0.0492   0.0774   1.0000
   7.500   1.0963   0.02834   0.01859  -0.0471   0.0723   1.0000
   7.750   1.1035   0.02954   0.01978  -0.0445   0.0684   1.0000
   8.000   1.1093   0.03096   0.02120  -0.0419   0.0664   1.0000
   8.250   1.1159   0.03262   0.02279  -0.0394   0.0648   1.0000
   8.500   1.1326   0.03426   0.02443  -0.0377   0.0634   1.0000
   8.750   1.1622   0.03610   0.02631  -0.0374   0.0604   1.0000
   9.000   1.2152   0.03890   0.02919  -0.0402   0.0589   1.0000
   9.250   1.2630   0.04263   0.03325  -0.0426   0.0591   1.0000
   9.500   1.2877   0.04590   0.03681  -0.0423   0.0581   1.0000
   9.750   1.3019   0.04975   0.04124  -0.0405   0.0593   1.0000
  10.000   1.3150   0.05464   0.04663  -0.0388   0.0624   1.0000
  10.250   1.3215   0.05918   0.05169  -0.0362   0.0661   1.0000
  10.500   1.3079   0.06479   0.05788  -0.0323   0.0709   1.0000
  11.000   1.2933   0.08244   0.07642  -0.0286   0.0926   1.0000
  11.250   1.2565   0.08403   0.07827  -0.0236   0.0929   1.0000
  11.500   1.2227   0.08701   0.08146  -0.0211   0.0931   1.0000
  11.750   1.1887   0.09112   0.08574  -0.0204   0.0933   1.0000
  12.000   1.1548   0.09634   0.09112  -0.0213   0.0933   1.0000
  12.250   1.1209   0.10262   0.09753  -0.0237   0.0933   1.0000
  12.500   1.0875   0.10992   0.10493  -0.0275   0.0933   1.0000
  12.750   1.0471   0.11953   0.11462  -0.0337   0.0933   1.0000
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