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

Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.84 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel430-il-1000000-n5.txt
Download as CSV file: xf-eiffel430-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8512   0.03092   0.02627  -0.1023   0.4914   0.0239
 -13.500  -0.8422   0.02791   0.02305  -0.1016   0.4808   0.0241
 -13.250  -0.8300   0.02618   0.02093  -0.1002   0.3783   0.0242
 -13.000  -0.8142   0.02498   0.01951  -0.0988   0.3057   0.0244
 -12.500  -0.7767   0.02295   0.01723  -0.0965   0.2942   0.0247
 -12.250  -0.7567   0.02212   0.01628  -0.0953   0.2907   0.0249
 -12.000  -0.7364   0.02133   0.01537  -0.0941   0.2876   0.0250
 -11.750  -0.7151   0.02064   0.01457  -0.0930   0.2846   0.0252
 -11.500  -0.6934   0.01999   0.01383  -0.0919   0.2828   0.0255
 -11.250  -0.6710   0.01942   0.01316  -0.0909   0.2808   0.0257
 -11.000  -0.6486   0.01885   0.01248  -0.0898   0.2788   0.0259
 -10.750  -0.6263   0.01825   0.01177  -0.0887   0.2768   0.0261
 -10.500  -0.6036   0.01770   0.01111  -0.0876   0.2748   0.0263
 -10.250  -0.5805   0.01718   0.01048  -0.0866   0.2730   0.0265
 -10.000  -0.5570   0.01672   0.00992  -0.0856   0.2713   0.0267
  -9.750  -0.5331   0.01628   0.00939  -0.0846   0.2702   0.0269
  -9.500  -0.5090   0.01586   0.00888  -0.0837   0.2688   0.0271
  -9.250  -0.4845   0.01549   0.00842  -0.0828   0.2672   0.0272
  -9.000  -0.4597   0.01515   0.00800  -0.0820   0.2657   0.0274
  -8.750  -0.4354   0.01474   0.00751  -0.0811   0.2644   0.0276
  -8.500  -0.4113   0.01431   0.00700  -0.0801   0.2631   0.0279
  -8.250  -0.3863   0.01399   0.00662  -0.0793   0.2618   0.0283
  -8.000  -0.3610   0.01372   0.00630  -0.0785   0.2604   0.0286
  -7.750  -0.3354   0.01349   0.00602  -0.0778   0.2590   0.0289
  -7.500  -0.3096   0.01327   0.00576  -0.0771   0.2580   0.0292
  -7.250  -0.2837   0.01306   0.00551  -0.0764   0.2574   0.0295
  -7.000  -0.2577   0.01286   0.00527  -0.0757   0.2567   0.0299
  -6.750  -0.2315   0.01269   0.00506  -0.0751   0.2559   0.0304
  -6.500  -0.2053   0.01251   0.00484  -0.0744   0.2551   0.0308
  -6.250  -0.1792   0.01233   0.00462  -0.0738   0.2542   0.0312
  -6.000  -0.1529   0.01217   0.00442  -0.0731   0.2533   0.0315
  -5.750  -0.1267   0.01202   0.00422  -0.0725   0.2524   0.0318
  -5.500  -0.1004   0.01186   0.00403  -0.0719   0.2515   0.0321
  -5.250  -0.0744   0.01166   0.00380  -0.0713   0.2506   0.0328
  -5.000  -0.0480   0.01153   0.00365  -0.0707   0.2498   0.0334
  -4.750  -0.0216   0.01141   0.00352  -0.0701   0.2489   0.0341
  -4.500   0.0048   0.01132   0.00341  -0.0695   0.2478   0.0347
  -4.250   0.0311   0.01124   0.00330  -0.0689   0.2459   0.0355
  -4.000   0.0576   0.01116   0.00319  -0.0684   0.2445   0.0362
  -3.750   0.0842   0.01108   0.00309  -0.0679   0.2437   0.0368
  -3.500   0.1107   0.01099   0.00300  -0.0673   0.2432   0.0377
  -3.250   0.1370   0.01090   0.00291  -0.0667   0.2425   0.0389
  -3.000   0.1634   0.01083   0.00285  -0.0662   0.2417   0.0402
  -2.750   0.1899   0.01078   0.00279  -0.0657   0.2409   0.0413
  -2.500   0.2163   0.01074   0.00274  -0.0651   0.2402   0.0424
  -2.250   0.2427   0.01070   0.00270  -0.0646   0.2393   0.0434
  -2.000   0.2688   0.01063   0.00263  -0.0640   0.2383   0.0454
  -1.750   0.2951   0.01058   0.00258  -0.0635   0.2370   0.0471
  -1.500   0.3214   0.01055   0.00254  -0.0630   0.2359   0.0490
  -1.250   0.3476   0.01054   0.00252  -0.0624   0.2349   0.0510
  -1.000   0.3735   0.01050   0.00249  -0.0619   0.2339   0.0546
  -0.500   0.4241   0.01041   0.00251  -0.0605   0.2317   0.0855
  -0.250   0.4502   0.01039   0.00253  -0.0600   0.2308   0.0983
   0.000   0.4761   0.01038   0.00255  -0.0595   0.2301   0.1059
   0.250   0.5021   0.01039   0.00258  -0.0589   0.2293   0.1116
   0.500   0.5281   0.01040   0.00262  -0.0584   0.2283   0.1175
   1.000   0.5795   0.01042   0.00276  -0.0574   0.2260   0.1509
   1.250   0.6055   0.01047   0.00284  -0.0569   0.2247   0.1636
   1.500   0.6316   0.01052   0.00289  -0.0564   0.2232   0.1698
   1.750   0.6575   0.01057   0.00296  -0.0559   0.2215   0.1740
   2.000   0.6833   0.01062   0.00302  -0.0555   0.2198   0.1778
   2.250   0.7089   0.01070   0.00309  -0.0549   0.2179   0.1807
   2.500   0.7347   0.01076   0.00317  -0.0545   0.2166   0.1840
   2.750   0.7603   0.01080   0.00325  -0.0540   0.2139   0.1885
   3.000   0.7861   0.01085   0.00330  -0.0535   0.2087   0.1909
   3.250   0.8113   0.01091   0.00334  -0.0530   0.2026   0.1925
   3.500   0.8344   0.01108   0.00338  -0.0521   0.1768   0.1939
   3.750   0.8454   0.01182   0.00385  -0.0491   0.1220   0.1948
   4.000   0.8665   0.01206   0.00406  -0.0478   0.1158   0.1958
   4.250   0.8881   0.01227   0.00426  -0.0467   0.1108   0.1965
   4.500   0.9105   0.01242   0.00443  -0.0456   0.1087   0.1986
   4.750   0.9325   0.01258   0.00461  -0.0446   0.1069   0.2006
   5.000   0.9542   0.01274   0.00479  -0.0435   0.1054   0.2018
   5.250   0.9753   0.01293   0.00500  -0.0422   0.1036   0.2033
   5.500   0.9959   0.01313   0.00521  -0.0409   0.1019   0.2045
   5.750   1.0162   0.01334   0.00542  -0.0396   0.1001   0.2059
   6.000   1.0351   0.01354   0.00564  -0.0380   0.0980   0.2072
   6.250   1.0527   0.01374   0.00587  -0.0361   0.0963   0.2088
   6.750   1.0904   0.01406   0.00626  -0.0329   0.0945   0.2143
   7.000   1.1089   0.01426   0.00650  -0.0312   0.0934   0.2175
   7.250   1.1274   0.01447   0.00675  -0.0297   0.0920   0.2202
   7.500   1.1453   0.01472   0.00703  -0.0280   0.0901   0.2229
   8.000   1.1800   0.01529   0.00763  -0.0246   0.0857   0.2342
   8.250   1.1968   0.01558   0.00797  -0.0229   0.0836   0.2571
   8.750   1.3589   0.01583   0.00951  -0.0484   0.0668   0.9995
   9.000   1.3801   0.01626   0.00991  -0.0477   0.0632   1.0000
   9.250   1.3942   0.01661   0.01027  -0.0455   0.0613   1.0000
   9.500   1.4081   0.01701   0.01067  -0.0434   0.0590   1.0000
   9.750   1.4219   0.01745   0.01112  -0.0413   0.0569   1.0000
  10.000   1.4356   0.01793   0.01159  -0.0393   0.0545   1.0000
  10.250   1.4505   0.01836   0.01205  -0.0376   0.0533   1.0000
  10.500   1.4654   0.01881   0.01253  -0.0359   0.0523   1.0000
  10.750   1.4797   0.01931   0.01306  -0.0342   0.0509   1.0000
  11.000   1.4936   0.01987   0.01364  -0.0325   0.0494   1.0000
  11.250   1.5070   0.02049   0.01426  -0.0309   0.0478   1.0000
  11.500   1.5206   0.02111   0.01491  -0.0293   0.0465   1.0000
  11.750   1.5348   0.02170   0.01554  -0.0279   0.0457   1.0000
  12.000   1.5490   0.02230   0.01620  -0.0265   0.0449   1.0000
  12.250   1.5623   0.02299   0.01691  -0.0252   0.0432   1.0000
  12.500   1.5747   0.02375   0.01770  -0.0238   0.0417   1.0000
  12.750   1.5862   0.02460   0.01857  -0.0224   0.0400   1.0000
  13.000   1.5979   0.02545   0.01945  -0.0210   0.0382   1.0000
  13.250   1.6090   0.02636   0.02039  -0.0198   0.0357   1.0000
  13.500   1.6179   0.02747   0.02150  -0.0184   0.0329   1.0000
  13.750   1.6249   0.02874   0.02277  -0.0170   0.0284   1.0000
  14.000   1.6195   0.03106   0.02501  -0.0148   0.0183   1.0000
  14.250   1.6216   0.03285   0.02685  -0.0134   0.0159   1.0000
  14.500   1.6250   0.03461   0.02866  -0.0123   0.0146   1.0000
  14.750   1.6277   0.03650   0.03062  -0.0113   0.0135   1.0000
  15.000   1.6320   0.03829   0.03248  -0.0106   0.0130   1.0000
  15.250   1.6344   0.04034   0.03460  -0.0099   0.0124   1.0000
  15.500   1.6352   0.04262   0.03696  -0.0093   0.0119   1.0000
  15.750   1.6350   0.04507   0.03948  -0.0089   0.0114   1.0000
  16.000   1.6349   0.04758   0.04207  -0.0086   0.0110   1.0000
  16.250   1.6356   0.05006   0.04465  -0.0085   0.0108   1.0000
  16.500   1.6345   0.05280   0.04747  -0.0084   0.0106   1.0000
  16.750   1.6308   0.05587   0.05063  -0.0085   0.0102   1.0000
  17.000   1.6259   0.05917   0.05403  -0.0086   0.0100   1.0000
  17.250   1.6188   0.06283   0.05779  -0.0090   0.0098   1.0000
  17.500   1.6099   0.06681   0.06189  -0.0095   0.0097   1.0000
  17.750   1.5973   0.07144   0.06663  -0.0104   0.0095   1.0000
  18.000   1.5797   0.07699   0.07231  -0.0117   0.0093   1.0000
  18.250   1.5593   0.08332   0.07880  -0.0136   0.0093   1.0000
  18.500   1.5358   0.09112   0.08678  -0.0165   0.0093   1.0000
  18.750   1.4732   0.10670   0.10263  -0.0239   0.0096   1.0000
  19.000   1.4360   0.11648   0.11255  -0.0282   0.0097   1.0000
<< Back to Eiffel 430 (Lachassgne) (eiffel430-il)

Polar data table (+)

Polar graphs


<< Back to Eiffel 430 (Lachassgne) (eiffel430-il)