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E423 (e423-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E423 (e423-il)
Reynolds number: 500,000
Max Cl/Cd: 123.42 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e423-il-500000.txt
Download as CSV file: xf-e423-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E423                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.3483   0.08971   0.08619  -0.1735   0.8041   0.0196
  -9.750   0.3588   0.08785   0.08423  -0.1733   0.7873   0.0197
  -9.500   0.3680   0.08620   0.08249  -0.1731   0.7726   0.0201
  -9.250   0.3761   0.08448   0.08068  -0.1732   0.7603   0.0202
  -9.000   0.3840   0.08276   0.07891  -0.1732   0.7493   0.0206
  -8.750   0.3918   0.08095   0.07704  -0.1733   0.7400   0.0210
  -8.500   0.3993   0.07913   0.07519  -0.1734   0.7314   0.0214
  -8.250   0.4061   0.07714   0.07314  -0.1738   0.7240   0.0222
  -8.000   0.4082   0.07503   0.07104  -0.1746   0.7169   0.0227
  -7.750   0.4088   0.07304   0.06903  -0.1753   0.7100   0.0228
  -7.500   0.4179   0.07087   0.06683  -0.1749   0.7041   0.0230
  -7.250   0.4298   0.06927   0.06523  -0.1742   0.6981   0.0233
  -7.000   0.4378   0.06772   0.06365  -0.1739   0.6924   0.0235
  -6.750   0.4461   0.06618   0.06206  -0.1737   0.6872   0.0239
  -6.500   0.4514   0.06458   0.06051  -0.1731   0.6825   0.0247
  -6.250   0.4544   0.06296   0.05890  -0.1723   0.6776   0.0253
  -6.000   0.4471   0.06080   0.05674  -0.1726   0.6729   0.0263
  -5.750   0.4518   0.02067   0.01569  -0.2281   0.6709   0.0153
  -5.500   0.4894   0.01736   0.01179  -0.2336   0.6668   0.0158
  -5.250   0.5198   0.01608   0.01018  -0.2352   0.6627   0.0163
  -5.000   0.5489   0.01508   0.00904  -0.2362   0.6585   0.0172
  -4.750   0.5782   0.01455   0.00835  -0.2368   0.6548   0.0179
  -4.500   0.6091   0.01408   0.00766  -0.2377   0.6509   0.0190
  -4.250   0.6371   0.01351   0.00702  -0.2380   0.6477   0.0202
  -4.000   0.6652   0.01318   0.00662  -0.2381   0.6440   0.0220
  -3.750   0.6935   0.01286   0.00622  -0.2384   0.6404   0.0246
  -3.500   0.7224   0.01263   0.00590  -0.2386   0.6370   0.0287
  -3.250   0.7528   0.01248   0.00562  -0.2392   0.6336   0.0351
  -3.000   0.7807   0.01224   0.00538  -0.2393   0.6307   0.0417
  -2.750   0.8078   0.01212   0.00525  -0.2392   0.6274   0.0483
  -2.500   0.8352   0.01203   0.00514  -0.2391   0.6241   0.0552
  -2.250   0.8631   0.01196   0.00503  -0.2391   0.6211   0.0620
  -2.000   0.8917   0.01193   0.00495  -0.2392   0.6181   0.0698
  -1.750   0.9219   0.01198   0.00494  -0.2398   0.6148   0.0787
  -1.500   0.9479   0.01195   0.00491  -0.2393   0.6121   0.0869
  -1.250   0.9746   0.01190   0.00489  -0.2391   0.6091   0.0966
  -1.000   1.0017   0.01188   0.00488  -0.2389   0.6062   0.1060
  -0.750   1.0290   0.01189   0.00486  -0.2388   0.6033   0.1151
  -0.500   1.0568   0.01197   0.00491  -0.2388   0.6004   0.1241
  -0.250   1.0871   0.01209   0.00498  -0.2394   0.5971   0.1336
   0.000   1.1123   0.01214   0.00504  -0.2388   0.5946   0.1418
   0.250   1.1382   0.01214   0.00508  -0.2384   0.5919   0.1514
   0.500   1.1643   0.01221   0.00514  -0.2381   0.5889   0.1595
   0.750   1.1907   0.01222   0.00516  -0.2378   0.5860   0.1689
   1.000   1.2176   0.01232   0.00521  -0.2377   0.5832   0.1771
   1.250   1.2470   0.01242   0.00530  -0.2381   0.5803   0.1869
   1.500   1.2732   0.01253   0.00541  -0.2378   0.5776   0.1955
   1.750   1.2977   0.01254   0.00548  -0.2372   0.5748   0.2049
   2.000   1.3227   0.01261   0.00556  -0.2367   0.5718   0.2140
   2.250   1.3483   0.01265   0.00564  -0.2363   0.5689   0.2247
   2.500   1.3743   0.01273   0.00572  -0.2360   0.5661   0.2360
   2.750   1.4024   0.01287   0.00584  -0.2362   0.5631   0.2491
   3.000   1.4288   0.01299   0.00601  -0.2361   0.5602   0.2647
   3.250   1.4517   0.01304   0.00615  -0.2352   0.5574   0.2820
   3.500   1.4754   0.01310   0.00628  -0.2345   0.5543   0.3058
   3.750   1.4997   0.01314   0.00643  -0.2339   0.5512   0.3432
   4.000   1.5251   0.01314   0.00661  -0.2337   0.5482   0.4374
   4.250   1.5496   0.01268   0.00686  -0.2333   0.5452   1.0000
   4.500   1.5725   0.01285   0.00703  -0.2324   0.5421   1.0000
   4.750   1.5925   0.01297   0.00718  -0.2309   0.5389   1.0000
   5.000   1.6130   0.01310   0.00731  -0.2296   0.5354   1.0000
   5.250   1.6339   0.01324   0.00743  -0.2283   0.5319   1.0000
   5.500   1.6587   0.01344   0.00757  -0.2279   0.5282   1.0000
   5.750   1.6786   0.01363   0.00779  -0.2265   0.5247   1.0000
   6.000   1.6956   0.01378   0.00798  -0.2245   0.5208   1.0000
   6.250   1.7141   0.01394   0.00815  -0.2228   0.5169   1.0000
   6.500   1.7344   0.01413   0.00832  -0.2215   0.5130   1.0000
   6.750   1.7566   0.01438   0.00855  -0.2207   0.5090   1.0000
   7.000   1.7723   0.01458   0.00882  -0.2185   0.5051   1.0000
   7.250   1.7889   0.01479   0.00907  -0.2166   0.5006   1.0000
   7.500   1.8074   0.01503   0.00929  -0.2150   0.4964   1.0000
   7.750   1.8266   0.01532   0.00959  -0.2137   0.4920   1.0000
   8.000   1.8411   0.01559   0.00994  -0.2114   0.4873   1.0000
   8.250   1.8568   0.01589   0.01026  -0.2095   0.4824   1.0000
   8.500   1.8743   0.01625   0.01058  -0.2079   0.4776   1.0000
   8.750   1.8885   0.01661   0.01102  -0.2057   0.4727   1.0000
   9.000   1.9027   0.01699   0.01146  -0.2036   0.4671   1.0000
   9.250   1.9167   0.01745   0.01189  -0.2015   0.4618   1.0000
   9.500   1.9301   0.01792   0.01244  -0.1994   0.4562   1.0000
   9.750   1.9426   0.01844   0.01300  -0.1971   0.4501   1.0000
  10.000   1.9537   0.01908   0.01361  -0.1947   0.4440   1.0000
  10.250   1.9655   0.01967   0.01431  -0.1925   0.4376   1.0000
  10.500   1.9751   0.02042   0.01506  -0.1901   0.4308   1.0000
  10.750   1.9848   0.02120   0.01589  -0.1877   0.4242   1.0000
  11.000   1.9930   0.02209   0.01682  -0.1852   0.4167   1.0000
  11.250   1.9999   0.02311   0.01786  -0.1826   0.4093   1.0000
  11.500   2.0065   0.02419   0.01899  -0.1801   0.4010   1.0000
  11.750   2.0108   0.02548   0.02029  -0.1775   0.3931   1.0000
  12.000   2.0146   0.02688   0.02173  -0.1749   0.3839   1.0000
  12.250   2.0177   0.02840   0.02328  -0.1724   0.3754   1.0000
  12.500   2.0177   0.03024   0.02513  -0.1697   0.3657   1.0000
  12.750   2.0190   0.03207   0.02700  -0.1673   0.3555   1.0000
  13.000   2.0159   0.03434   0.02927  -0.1647   0.3454   1.0000
  13.250   2.0128   0.03673   0.03168  -0.1623   0.3345   1.0000
  13.500   2.0095   0.03926   0.03423  -0.1601   0.3233   1.0000
  13.750   2.0030   0.04216   0.03714  -0.1578   0.3124   1.0000
  14.000   1.9938   0.04547   0.04044  -0.1555   0.3009   1.0000
  14.250   1.9887   0.04850   0.04349  -0.1538   0.2893   1.0000
  14.500   1.9812   0.05185   0.04686  -0.1520   0.2783   1.0000
  14.750   1.9712   0.05558   0.05058  -0.1503   0.2676   1.0000
  15.000   1.9631   0.05922   0.05423  -0.1488   0.2565   1.0000
  15.250   1.9564   0.06280   0.05783  -0.1476   0.2464   1.0000
  15.500   1.9467   0.06680   0.06183  -0.1464   0.2366   1.0000
  15.750   1.9403   0.07049   0.06554  -0.1455   0.2268   1.0000
  16.000   1.9349   0.07413   0.06921  -0.1447   0.2178   1.0000
  16.250   1.9250   0.07840   0.07347  -0.1439   0.2089   1.0000
  16.500   1.9225   0.08177   0.07689  -0.1434   0.2002   1.0000
  16.750   1.9145   0.08591   0.08103  -0.1429   0.1922   1.0000
  17.000   1.9107   0.08956   0.08472  -0.1426   0.1840   1.0000
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