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Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il)
Reynolds number: 50,000
Max Cl/Cd: 32.86 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel430-il-50000-n5.txt
Download as CSV file: xf-eiffel430-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 430 (Lachassgne)                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3190   0.11745   0.11061  -0.0329   1.0000   0.1274
 -10.500  -0.3248   0.11581   0.10908  -0.0336   1.0000   0.1277
 -10.250  -0.3311   0.11406   0.10744  -0.0339   1.0000   0.1279
 -10.000  -0.3173   0.10936   0.10280  -0.0327   1.0000   0.1287
  -9.750  -0.3086   0.10591   0.09941  -0.0315   1.0000   0.1298
  -9.500  -0.3057   0.10327   0.09686  -0.0305   1.0000   0.1310
  -9.250  -0.2998   0.10045   0.09412  -0.0307   0.9930   0.1326
  -9.000  -0.2845   0.09703   0.09071  -0.0339   0.9733   0.1360
  -8.750  -0.2802   0.09449   0.08821  -0.0392   0.9500   0.1409
  -8.500  -0.2744   0.09153   0.08523  -0.0465   0.9271   0.1422
  -8.000  -0.2403   0.07883   0.07230  -0.0561   0.8947   0.0967
  -7.750  -0.2237   0.07503   0.06843  -0.0585   0.8760   0.0936
  -7.250  -0.2042   0.06554   0.05857  -0.0676   0.8332   0.0863
  -7.000  -0.1910   0.06200   0.05486  -0.0694   0.8106   0.0865
  -6.750  -0.1735   0.05950   0.05229  -0.0696   0.7898   0.0879
  -6.500  -0.1553   0.05651   0.04911  -0.0707   0.7702   0.0886
  -6.250  -0.1379   0.05276   0.04504  -0.0723   0.7522   0.0880
  -6.000  -0.1206   0.04876   0.04063  -0.0734   0.7365   0.0872
  -5.750  -0.1020   0.04575   0.03726  -0.0736   0.7223   0.0872
  -5.500  -0.0823   0.04342   0.03465  -0.0732   0.7099   0.0879
  -5.250  -0.0621   0.04183   0.03287  -0.0726   0.6982   0.0898
  -5.000  -0.0418   0.03997   0.03072  -0.0720   0.6883   0.0923
  -4.750  -0.0216   0.03767   0.02803  -0.0713   0.6797   0.0944
  -4.500  -0.0007   0.03523   0.02514  -0.0706   0.6727   0.0958
  -4.250   0.0206   0.03276   0.02215  -0.0697   0.6655   0.0977
  -4.000   0.0437   0.03144   0.02057  -0.0689   0.6578   0.1008
  -3.750   0.0666   0.03075   0.01977  -0.0679   0.6502   0.1049
  -3.500   0.0909   0.02934   0.01800  -0.0671   0.6438   0.1098
  -3.250   0.1168   0.02790   0.01619  -0.0665   0.6376   0.1142
  -3.000   0.1409   0.02752   0.01580  -0.0656   0.6306   0.1200
  -2.750   0.1676   0.02664   0.01462  -0.0651   0.6239   0.1291
  -2.500   0.1928   0.02626   0.01420  -0.0643   0.6172   0.1368
  -2.250   0.2182   0.02584   0.01367  -0.0635   0.6085   0.1487
  -2.000   0.2456   0.02548   0.01310  -0.0630   0.6012   0.1653
  -1.750   0.2738   0.02514   0.01258  -0.0627   0.5939   0.1848
  -1.500   0.3021   0.02482   0.01214  -0.0626   0.5874   0.2049
  -1.250   0.3299   0.02449   0.01177  -0.0626   0.5813   0.2306
  -1.000   0.3600   0.02402   0.01131  -0.0630   0.5744   0.2509
  -0.750   0.3901   0.02360   0.01083  -0.0632   0.5661   0.2654
  -0.500   0.4177   0.02330   0.01054  -0.0630   0.5583   0.2766
  -0.250   0.4444   0.02301   0.01030  -0.0627   0.5504   0.2871
   0.000   0.4695   0.02278   0.01017  -0.0621   0.5418   0.3005
   0.250   0.4938   0.02260   0.01009  -0.0614   0.5322   0.3159
   0.500   0.5170   0.02245   0.01010  -0.0605   0.5189   0.3340
   0.750   0.5397   0.02226   0.01018  -0.0596   0.5037   0.3648
   1.000   0.6255   0.02108   0.01024  -0.0714   0.4129   1.0000
   1.250   0.6425   0.02146   0.00991  -0.0688   0.3922   1.0000
   1.500   0.6613   0.02190   0.00999  -0.0671   0.3851   1.0000
   1.750   0.6808   0.02234   0.01018  -0.0655   0.3805   1.0000
   2.000   0.7006   0.02278   0.01043  -0.0640   0.3771   1.0000
   2.250   0.7207   0.02322   0.01073  -0.0626   0.3744   1.0000
   2.500   0.7413   0.02367   0.01106  -0.0612   0.3720   1.0000
   2.750   0.7618   0.02415   0.01144  -0.0599   0.3691   1.0000
   3.000   0.7825   0.02472   0.01187  -0.0587   0.3653   1.0000
   3.250   0.8044   0.02535   0.01233  -0.0576   0.3606   1.0000
   3.500   0.8278   0.02598   0.01286  -0.0569   0.3550   1.0000
   3.750   0.8561   0.02673   0.01341  -0.0569   0.3491   1.0000
   4.000   0.8823   0.02734   0.01402  -0.0567   0.3437   1.0000
   4.250   0.9142   0.02807   0.01463  -0.0574   0.3384   1.0000
   4.500   0.9438   0.02878   0.01532  -0.0577   0.3339   1.0000
   4.750   0.9727   0.02960   0.01613  -0.0580   0.3275   1.0000
   5.000   1.0026   0.03057   0.01705  -0.0585   0.3208   1.0000
   5.250   1.0307   0.03159   0.01807  -0.0588   0.3132   1.0000
   5.500   1.0538   0.03258   0.01915  -0.0582   0.3054   1.0000
   5.750   1.0844   0.03383   0.02032  -0.0589   0.2980   1.0000
   6.000   1.1007   0.03461   0.02138  -0.0572   0.2916   1.0000
   6.250   1.1259   0.03581   0.02263  -0.0571   0.2840   1.0000
   6.500   1.1403   0.03670   0.02378  -0.0551   0.2755   1.0000
   6.750   1.1555   0.03768   0.02497  -0.0533   0.2666   1.0000
   7.000   1.1729   0.03865   0.02604  -0.0519   0.2574   1.0000
   7.250   1.1819   0.03946   0.02716  -0.0492   0.2476   1.0000
   7.500   1.1896   0.04029   0.02827  -0.0463   0.2376   1.0000
   7.750   1.1987   0.04103   0.02919  -0.0437   0.2281   1.0000
   8.000   1.2071   0.04167   0.03001  -0.0410   0.2190   1.0000
   8.250   1.2114   0.04269   0.03131  -0.0379   0.2088   1.0000
   8.500   1.2183   0.04353   0.03234  -0.0352   0.2005   1.0000
   8.750   1.2249   0.04426   0.03321  -0.0325   0.1932   1.0000
   9.000   1.2305   0.04537   0.03449  -0.0299   0.1861   1.0000
   9.250   1.2354   0.04610   0.03531  -0.0270   0.1806   1.0000
   9.500   1.2387   0.04696   0.03625  -0.0241   0.1756   1.0000
   9.750   1.2409   0.04823   0.03767  -0.0214   0.1702   1.0000
  10.000   1.2455   0.04897   0.03845  -0.0189   0.1664   1.0000
  10.250   1.2490   0.05048   0.04005  -0.0168   0.1625   1.0000
  10.500   1.2498   0.05243   0.04217  -0.0148   0.1584   1.0000
  10.750   1.2532   0.05385   0.04364  -0.0130   0.1551   1.0000
  11.000   1.2608   0.05475   0.04449  -0.0114   0.1523   1.0000
  11.250   1.2543   0.05783   0.04780  -0.0098   0.1488   1.0000
  11.500   1.2462   0.06095   0.05111  -0.0084   0.1457   1.0000
  11.750   1.2397   0.06380   0.05409  -0.0073   0.1430   1.0000
  12.000   1.2422   0.06576   0.05609  -0.0064   0.1406   1.0000
  12.250   1.2497   0.06741   0.05770  -0.0056   0.1384   1.0000
  12.500   1.2112   0.07465   0.06528  -0.0059   0.1372   1.0000
  12.750   1.1280   0.08948   0.08044  -0.0106   0.1365   1.0000
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