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Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il)
Reynolds number: 500,000
Max Cl/Cd: 71.37 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel430-il-500000-n5.txt
Download as CSV file: xf-eiffel430-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5339   0.03119   0.02531  -0.0923   0.2929   0.0290
 -10.250  -0.5242   0.02807   0.02185  -0.0913   0.2913   0.0293
 -10.000  -0.5098   0.02613   0.01965  -0.0900   0.2894   0.0296
  -9.750  -0.4934   0.02456   0.01783  -0.0886   0.2876   0.0299
  -9.500  -0.4755   0.02324   0.01628  -0.0873   0.2857   0.0302
  -9.250  -0.4562   0.02212   0.01494  -0.0860   0.2842   0.0306
  -9.000  -0.4356   0.02114   0.01376  -0.0848   0.2827   0.0309
  -8.750  -0.4142   0.02029   0.01273  -0.0836   0.2809   0.0312
  -8.500  -0.3920   0.01955   0.01182  -0.0825   0.2791   0.0315
  -8.250  -0.3690   0.01893   0.01104  -0.0815   0.2775   0.0318
  -8.000  -0.3458   0.01834   0.01030  -0.0805   0.2760   0.0320
  -7.750  -0.3231   0.01767   0.00953  -0.0794   0.2746   0.0324
  -7.500  -0.2992   0.01724   0.00903  -0.0785   0.2732   0.0328
  -7.250  -0.2748   0.01693   0.00865  -0.0776   0.2719   0.0332
  -7.000  -0.2499   0.01663   0.00830  -0.0768   0.2709   0.0337
  -6.750  -0.2249   0.01633   0.00794  -0.0760   0.2700   0.0342
  -6.500  -0.1999   0.01599   0.00753  -0.0752   0.2689   0.0347
  -6.250  -0.1748   0.01566   0.00713  -0.0744   0.2679   0.0352
  -6.000  -0.1497   0.01536   0.00675  -0.0736   0.2668   0.0357
  -5.750  -0.1244   0.01508   0.00640  -0.0729   0.2658   0.0363
  -5.500  -0.0990   0.01483   0.00608  -0.0721   0.2647   0.0367
  -5.250  -0.0734   0.01463   0.00581  -0.0714   0.2638   0.0371
  -5.000  -0.0485   0.01430   0.00546  -0.0706   0.2628   0.0379
  -4.750  -0.0232   0.01410   0.00523  -0.0699   0.2619   0.0386
  -4.500   0.0024   0.01395   0.00506  -0.0692   0.2611   0.0393
  -4.250   0.0279   0.01383   0.00490  -0.0684   0.2601   0.0403
  -4.000   0.0532   0.01374   0.00477  -0.0677   0.2590   0.0414
  -3.750   0.0787   0.01365   0.00465  -0.0670   0.2581   0.0424
  -3.500   0.1045   0.01355   0.00452  -0.0663   0.2574   0.0431
  -3.250   0.1299   0.01334   0.00432  -0.0656   0.2564   0.0444
  -3.000   0.1557   0.01320   0.00418  -0.0650   0.2549   0.0458
  -2.750   0.1815   0.01311   0.00407  -0.0643   0.2535   0.0472
  -2.500   0.2073   0.01303   0.00398  -0.0637   0.2523   0.0488
  -2.250   0.2329   0.01299   0.00392  -0.0630   0.2514   0.0503
  -2.000   0.2581   0.01289   0.00382  -0.0623   0.2506   0.0532
  -1.750   0.2834   0.01284   0.00377  -0.0616   0.2498   0.0559
  -1.500   0.3087   0.01281   0.00373  -0.0608   0.2490   0.0593
  -1.250   0.3336   0.01275   0.00371  -0.0601   0.2482   0.0657
  -1.000   0.3581   0.01267   0.00375  -0.0593   0.2474   0.0946
  -0.750   0.3829   0.01269   0.00378  -0.0585   0.2466   0.1071
  -0.500   0.4075   0.01274   0.00384  -0.0577   0.2454   0.1170
  -0.250   0.4323   0.01277   0.00390  -0.0570   0.2445   0.1257
   0.000   0.4579   0.01277   0.00398  -0.0564   0.2434   0.1393
   0.250   0.4836   0.01282   0.00408  -0.0558   0.2420   0.1540
   0.500   0.5090   0.01289   0.00418  -0.0552   0.2409   0.1642
   0.750   0.5343   0.01298   0.00428  -0.0546   0.2399   0.1720
   1.000   0.5596   0.01307   0.00439  -0.0540   0.2389   0.1783
   1.250   0.5847   0.01316   0.00446  -0.0533   0.2378   0.1825
   1.500   0.6096   0.01322   0.00455  -0.0526   0.2367   0.1865
   1.750   0.6346   0.01330   0.00464  -0.0520   0.2356   0.1911
   2.000   0.6596   0.01339   0.00473  -0.0514   0.2344   0.1957
   2.250   0.6839   0.01345   0.00480  -0.0506   0.2332   0.1988
   2.500   0.7078   0.01353   0.00489  -0.0498   0.2320   0.2011
   2.750   0.7320   0.01360   0.00499  -0.0491   0.2308   0.2036
   3.000   0.7564   0.01367   0.00510  -0.0484   0.2295   0.2063
   3.250   0.7806   0.01374   0.00521  -0.0476   0.2279   0.2084
   3.500   0.8048   0.01381   0.00531  -0.0469   0.2261   0.2100
   3.750   0.8295   0.01383   0.00536  -0.0463   0.2232   0.2115
   4.000   0.8546   0.01378   0.00532  -0.0457   0.2193   0.2140
   4.250   0.8788   0.01381   0.00540  -0.0450   0.2151   0.2169
   4.500   0.9030   0.01385   0.00549  -0.0444   0.2096   0.2191
   4.750   0.9272   0.01388   0.00552  -0.0437   0.2032   0.2210
   5.000   0.9509   0.01393   0.00555  -0.0429   0.1897   0.2232
   5.500   0.9772   0.01492   0.00612  -0.0379   0.1218   0.2288
   5.750   0.9932   0.01519   0.00640  -0.0358   0.1179   0.2329
   6.000   1.0089   0.01548   0.00671  -0.0336   0.1144   0.2371
   6.500   1.0422   0.01605   0.00737  -0.0297   0.1094   0.2537
   6.750   1.0525   0.01580   0.00776  -0.0267   0.1080   0.6024
   7.750   1.2490   0.01750   0.01033  -0.0483   0.0951   1.0000
   8.250   1.2786   0.01815   0.01106  -0.0440   0.0917   1.0000
   8.500   1.2933   0.01853   0.01146  -0.0420   0.0895   1.0000
   8.750   1.3076   0.01897   0.01192  -0.0400   0.0872   1.0000
   9.000   1.3212   0.01948   0.01244  -0.0379   0.0849   1.0000
   9.250   1.3361   0.01994   0.01293  -0.0362   0.0827   1.0000
   9.500   1.3521   0.02036   0.01339  -0.0346   0.0796   1.0000
   9.750   1.3671   0.02086   0.01389  -0.0330   0.0760   1.0000
  10.000   1.3813   0.02145   0.01446  -0.0314   0.0729   1.0000
  10.250   1.3959   0.02200   0.01505  -0.0298   0.0704   1.0000
  10.500   1.4099   0.02261   0.01569  -0.0283   0.0680   1.0000
  10.750   1.4234   0.02330   0.01637  -0.0268   0.0652   1.0000
  11.000   1.4362   0.02404   0.01712  -0.0253   0.0630   1.0000
  11.250   1.4494   0.02474   0.01789  -0.0238   0.0612   1.0000
  11.500   1.4619   0.02553   0.01871  -0.0224   0.0594   1.0000
  11.750   1.4737   0.02638   0.01960  -0.0210   0.0577   1.0000
  12.000   1.4847   0.02732   0.02056  -0.0196   0.0561   1.0000
  12.250   1.4950   0.02832   0.02161  -0.0182   0.0549   1.0000
  12.500   1.5055   0.02933   0.02268  -0.0170   0.0537   1.0000
  12.750   1.5163   0.03033   0.02377  -0.0158   0.0527   1.0000
  13.000   1.5267   0.03140   0.02490  -0.0147   0.0512   1.0000
  13.250   1.5359   0.03261   0.02616  -0.0136   0.0496   1.0000
  13.500   1.5440   0.03392   0.02753  -0.0126   0.0483   1.0000
  13.750   1.5508   0.03540   0.02906  -0.0116   0.0470   1.0000
  14.000   1.5576   0.03691   0.03064  -0.0108   0.0458   1.0000
  14.250   1.5664   0.03828   0.03210  -0.0101   0.0444   1.0000
  14.500   1.5732   0.03985   0.03376  -0.0094   0.0430   1.0000
  14.750   1.5778   0.04170   0.03564  -0.0088   0.0403   1.0000
  15.000   1.5821   0.04362   0.03763  -0.0083   0.0384   1.0000
  15.250   1.5865   0.04557   0.03967  -0.0079   0.0361   1.0000
  15.500   1.5874   0.04794   0.04207  -0.0076   0.0327   1.0000
  15.750   1.5852   0.05071   0.04487  -0.0073   0.0278   1.0000
  16.000   1.5769   0.05424   0.04843  -0.0073   0.0225   1.0000
  16.250   1.5674   0.05802   0.05227  -0.0073   0.0201   1.0000
  16.500   1.5559   0.06218   0.05652  -0.0077   0.0185   1.0000
  16.750   1.5414   0.06688   0.06133  -0.0083   0.0172   1.0000
  17.000   1.5265   0.07182   0.06640  -0.0092   0.0165   1.0000
  17.250   1.5103   0.07724   0.07197  -0.0105   0.0161   1.0000
  17.500   1.4899   0.08369   0.07858  -0.0125   0.0160   1.0000
  17.750   1.4677   0.09141   0.08650  -0.0155   0.0158   1.0000
  18.000   1.4321   0.10220   0.09749  -0.0206   0.0159   1.0000
  18.250   1.4031   0.11075   0.10617  -0.0244   0.0160   1.0000
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