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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 500,000
Max Cl/Cd: 107.4 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e420-il-500000.txt
Download as CSV file: xf-e420-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 420 AIRFOIL                              
  
 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   0.3957   0.09252   0.08817  -0.1652   0.6696   0.0216
  -9.750   0.4033   0.09056   0.08618  -0.1656   0.6612   0.0222
  -9.500   0.4109   0.08866   0.08424  -0.1659   0.6529   0.0224
  -9.250   0.4130   0.08660   0.08213  -0.1668   0.6456   0.0228
  -9.000   0.4176   0.08474   0.08027  -0.1674   0.6390   0.0229
  -8.750   0.4214   0.08261   0.07813  -0.1678   0.6323   0.0230
  -8.500   0.4341   0.08068   0.07614  -0.1673   0.6255   0.0231
  -8.250   0.4451   0.07894   0.07440  -0.1670   0.6197   0.0233
  -8.000   0.4544   0.07733   0.07278  -0.1668   0.6139   0.0236
  -7.750   0.4624   0.07578   0.07118  -0.1667   0.6084   0.0238
  -7.500   0.4705   0.07415   0.06955  -0.1666   0.6037   0.0243
  -7.250   0.4776   0.07246   0.06788  -0.1665   0.5991   0.0246
  -7.000   0.4837   0.07077   0.06618  -0.1662   0.5944   0.0252
  -6.750   0.4880   0.06906   0.06445  -0.1659   0.5901   0.0258
  -6.500   0.4736   0.06703   0.06244  -0.1656   0.5864   0.0265
  -6.250   0.4699   0.06545   0.06091  -0.1642   0.5831   0.0265
  -6.000   0.4809   0.06382   0.05930  -0.1627   0.5788   0.0267
  -5.750   0.4894   0.06252   0.05800  -0.1615   0.5748   0.0269
  -5.500   0.4973   0.06122   0.05667  -0.1608   0.5710   0.0273
  -5.250   0.5060   0.05976   0.05517  -0.1608   0.5671   0.0277
  -5.000   0.5133   0.05812   0.05358  -0.1609   0.5645   0.0284
  -4.750   0.5215   0.05617   0.05166  -0.1617   0.5615   0.0292
  -4.500   0.6158   0.01781   0.01167  -0.2271   0.5614   0.0179
  -4.250   0.6477   0.01663   0.01020  -0.2287   0.5579   0.0183
  -4.000   0.6783   0.01584   0.00914  -0.2297   0.5545   0.0189
  -3.750   0.7083   0.01533   0.00839  -0.2303   0.5511   0.0195
  -3.500   0.7395   0.01479   0.00771  -0.2313   0.5475   0.0203
  -3.250   0.7676   0.01444   0.00734  -0.2314   0.5450   0.0214
  -3.000   0.7960   0.01414   0.00694  -0.2315   0.5421   0.0224
  -2.750   0.8247   0.01380   0.00655  -0.2318   0.5391   0.0237
  -2.500   0.8530   0.01361   0.00629  -0.2319   0.5363   0.0256
  -2.250   0.8817   0.01346   0.00607  -0.2321   0.5336   0.0291
  -2.000   0.9116   0.01334   0.00587  -0.2326   0.5307   0.0354
  -1.750   0.9417   0.01322   0.00574  -0.2330   0.5281   0.0475
  -1.500   0.9690   0.01310   0.00565  -0.2329   0.5262   0.0616
  -1.250   0.9960   0.01308   0.00564  -0.2328   0.5239   0.0746
  -1.000   1.0229   0.01308   0.00566  -0.2326   0.5214   0.0872
  -0.750   1.0497   0.01310   0.00569  -0.2324   0.5190   0.0990
  -0.500   1.0766   0.01315   0.00573  -0.2322   0.5167   0.1110
  -0.250   1.1042   0.01324   0.00579  -0.2321   0.5144   0.1231
   0.000   1.1331   0.01339   0.00589  -0.2324   0.5120   0.1347
   0.250   1.1625   0.01358   0.00605  -0.2328   0.5097   0.1460
   0.500   1.1882   0.01360   0.00613  -0.2323   0.5082   0.1570
   0.750   1.2138   0.01367   0.00620  -0.2319   0.5063   0.1672
   1.000   1.2395   0.01375   0.00631  -0.2315   0.5041   0.1778
   1.250   1.2654   0.01382   0.00638  -0.2312   0.5020   0.1881
   1.500   1.2915   0.01394   0.00650  -0.2309   0.5001   0.1985
   1.750   1.3177   0.01403   0.00659  -0.2306   0.4982   0.2087
   2.000   1.3443   0.01418   0.00672  -0.2305   0.4963   0.2189
   2.250   1.3726   0.01435   0.00688  -0.2307   0.4943   0.2294
   2.500   1.4039   0.01466   0.00713  -0.2316   0.4917   0.2403
   2.750   1.4272   0.01471   0.00726  -0.2308   0.4903   0.2508
   3.000   1.4506   0.01482   0.00739  -0.2300   0.4887   0.2608
   3.250   1.4747   0.01491   0.00755  -0.2294   0.4869   0.2727
   3.500   1.4989   0.01503   0.00770  -0.2288   0.4852   0.2850
   3.750   1.5231   0.01516   0.00786  -0.2283   0.4834   0.2985
   4.000   1.5474   0.01527   0.00803  -0.2278   0.4815   0.3150
   4.250   1.5717   0.01539   0.00819  -0.2272   0.4796   0.3348
   4.500   1.5970   0.01553   0.00838  -0.2270   0.4777   0.3633
   4.750   1.6266   0.01569   0.00868  -0.2277   0.4757   0.4397
   5.000   1.6560   0.01545   0.00913  -0.2284   0.4735   1.0000
   5.250   1.6754   0.01560   0.00931  -0.2270   0.4723   1.0000
   5.500   1.6947   0.01578   0.00952  -0.2255   0.4706   1.0000
   5.750   1.7150   0.01598   0.00973  -0.2242   0.4688   1.0000
   6.000   1.7362   0.01618   0.00996  -0.2232   0.4669   1.0000
   6.250   1.7581   0.01640   0.01018  -0.2223   0.4651   1.0000
   6.500   1.7801   0.01661   0.01038  -0.2214   0.4632   1.0000
   6.750   1.8022   0.01683   0.01059  -0.2206   0.4613   1.0000
   7.000   1.8255   0.01708   0.01083  -0.2201   0.4593   1.0000
   7.250   1.8552   0.01744   0.01115  -0.2209   0.4568   1.0000
   7.500   1.8751   0.01775   0.01149  -0.2197   0.4549   1.0000
   7.750   1.8897   0.01798   0.01179  -0.2175   0.4531   1.0000
   8.000   1.9054   0.01824   0.01212  -0.2156   0.4510   1.0000
   8.250   1.9223   0.01850   0.01242  -0.2139   0.4487   1.0000
   8.500   1.9403   0.01876   0.01270  -0.2125   0.4463   1.0000
   8.750   1.9587   0.01902   0.01297  -0.2111   0.4440   1.0000
   9.000   1.9783   0.01931   0.01326  -0.2101   0.4416   1.0000
   9.250   2.0061   0.01969   0.01360  -0.2106   0.4385   1.0000
   9.500   2.0139   0.02007   0.01409  -0.2074   0.4365   1.0000
   9.750   2.0245   0.02048   0.01460  -0.2048   0.4340   1.0000
  10.000   2.0369   0.02088   0.01506  -0.2026   0.4312   1.0000
  10.250   2.0509   0.02129   0.01550  -0.2007   0.4285   1.0000
  10.500   2.0656   0.02170   0.01594  -0.1990   0.4259   1.0000
  10.750   2.0858   0.02209   0.01631  -0.1983   0.4229   1.0000
  11.000   2.0971   0.02269   0.01699  -0.1962   0.4202   1.0000
  11.250   2.1031   0.02341   0.01782  -0.1933   0.4173   1.0000
  11.500   2.1115   0.02410   0.01860  -0.1909   0.4141   1.0000
  11.750   2.1211   0.02479   0.01934  -0.1887   0.4109   1.0000
  12.000   2.1335   0.02545   0.02001  -0.1870   0.4077   1.0000
  12.250   2.1448   0.02623   0.02083  -0.1853   0.4042   1.0000
  12.500   2.1466   0.02741   0.02215  -0.1824   0.4006   1.0000
  12.750   2.1510   0.02856   0.02338  -0.1800   0.3966   1.0000
  13.000   2.1579   0.02965   0.02450  -0.1780   0.3927   1.0000
  13.250   2.1664   0.03075   0.02562  -0.1763   0.3886   1.0000
  13.500   2.1656   0.03248   0.02749  -0.1738   0.3841   1.0000
  13.750   2.1672   0.03416   0.02924  -0.1717   0.3792   1.0000
  14.000   2.1714   0.03571   0.03078  -0.1699   0.3745   1.0000
  14.250   2.1699   0.03785   0.03306  -0.1679   0.3693   1.0000
  14.500   2.1683   0.04008   0.03536  -0.1660   0.3634   1.0000
  14.750   2.1668   0.04235   0.03764  -0.1642   0.3578   1.0000
  15.000   2.1614   0.04519   0.04061  -0.1624   0.3510   1.0000
  15.250   2.1549   0.04817   0.04360  -0.1607   0.3443   1.0000
  15.500   2.1471   0.05148   0.04701  -0.1591   0.3370   1.0000
  15.750   2.1357   0.05519   0.05074  -0.1576   0.3291   1.0000
  16.000   2.1241   0.05918   0.05482  -0.1563   0.3208   1.0000
  16.250   2.1089   0.06359   0.05923  -0.1549   0.3121   1.0000
  16.500   2.0936   0.06825   0.06397  -0.1539   0.3027   1.0000
  16.750   2.0772   0.07311   0.06886  -0.1530   0.2935   1.0000
  17.000   2.0578   0.07845   0.07419  -0.1522   0.2834   1.0000
  17.250   2.0421   0.08348   0.07929  -0.1517   0.2735   1.0000
  17.500   2.0259   0.08862   0.08443  -0.1513   0.2639   1.0000
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