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

EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 100,000
Max Cl/Cd: 45.86 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e403-il-100000-n5.txt
Download as CSV file: xf-e403-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5564   0.09191   0.08701  -0.0571   0.9971   0.0222
 -10.750  -0.5842   0.08247   0.07742  -0.0641   0.9946   0.0218
 -10.500  -0.6083   0.07592   0.07072  -0.0680   0.9915   0.0216
 -10.250  -0.6317   0.07042   0.06502  -0.0705   0.9883   0.0213
 -10.000  -0.6517   0.06558   0.05992  -0.0727   0.9849   0.0210
  -9.750  -0.6738   0.06231   0.05646  -0.0716   0.9801   0.0209
  -9.500  -0.6890   0.05938   0.05332  -0.0710   0.9758   0.0209
  -9.250  -0.6941   0.05558   0.04916  -0.0719   0.9720   0.0208
  -9.000  -0.6967   0.05296   0.04629  -0.0706   0.9679   0.0210
  -8.750  -0.6909   0.05028   0.04331  -0.0704   0.9645   0.0214
  -8.500  -0.6782   0.04759   0.04028  -0.0710   0.9617   0.0220
  -8.250  -0.6609   0.04494   0.03724  -0.0718   0.9596   0.0227
  -8.000  -0.6512   0.04279   0.03476  -0.0703   0.9565   0.0231
  -7.750  -0.6352   0.04069   0.03235  -0.0695   0.9536   0.0233
  -7.500  -0.6148   0.03878   0.03015  -0.0691   0.9512   0.0235
  -7.250  -0.5921   0.03710   0.02820  -0.0687   0.9492   0.0239
  -7.000  -0.5682   0.03571   0.02661  -0.0685   0.9476   0.0242
  -6.750  -0.5425   0.03450   0.02526  -0.0685   0.9461   0.0247
  -6.500  -0.5236   0.03335   0.02412  -0.0675   0.9434   0.0254
  -6.250  -0.5067   0.03241   0.02316  -0.0663   0.9402   0.0262
  -6.000  -0.4853   0.03155   0.02224  -0.0660   0.9374   0.0276
  -5.750  -0.4602   0.03077   0.02135  -0.0664   0.9349   0.0297
  -5.500  -0.4332   0.02986   0.02040  -0.0674   0.9329   0.0321
  -5.250  -0.4033   0.02907   0.01954  -0.0689   0.9312   0.0349
  -5.000  -0.3828   0.02840   0.01872  -0.0684   0.9276   0.0379
  -4.750  -0.3582   0.02761   0.01792  -0.0689   0.9243   0.0443
  -4.500  -0.3286   0.02657   0.01711  -0.0707   0.9219   0.0775
  -4.250  -0.2877   0.02380   0.01586  -0.0776   0.9211   0.3450
  -4.000  -0.2643   0.02466   0.01766  -0.0755   0.9182   0.5469
  -3.750  -0.2364   0.02597   0.01887  -0.0743   0.9157   0.5906
  -3.500  -0.2242   0.02671   0.01956  -0.0705   0.9099   0.6071
  -3.250  -0.2020   0.02749   0.02023  -0.0685   0.9060   0.6224
  -3.000  -0.1710   0.02787   0.02043  -0.0691   0.9034   0.6353
  -2.750  -0.1417   0.02819   0.02065  -0.0688   0.9012   0.6393
  -2.500  -0.1259   0.02823   0.02058  -0.0669   0.8951   0.6441
  -2.250  -0.0912   0.02804   0.02019  -0.0695   0.8917   0.6513
  -2.000  -0.0617   0.02811   0.02017  -0.0698   0.8888   0.6540
  -1.750  -0.0282   0.02815   0.02010  -0.0711   0.8866   0.6573
  -1.500  -0.0086   0.02811   0.01998  -0.0703   0.8801   0.6614
  -1.250   0.0270   0.02794   0.01966  -0.0729   0.8765   0.6669
  -1.000   0.0589   0.02793   0.01959  -0.0738   0.8734   0.6692
  -0.750   0.0863   0.02793   0.01955  -0.0740   0.8691   0.6719
  -0.500   0.1106   0.02792   0.01949  -0.0739   0.8629   0.6753
  -0.250   0.1462   0.02780   0.01930  -0.0759   0.8595   0.6790
   0.000   0.1870   0.02762   0.01903  -0.0791   0.8572   0.6832
   0.250   0.2035   0.02768   0.01910  -0.0773   0.8485   0.6855
   0.500   0.2372   0.02755   0.01897  -0.0785   0.8447   0.6880
   0.750   0.2641   0.02750   0.01891  -0.0788   0.8385   0.6910
   1.000   0.2949   0.02737   0.01878  -0.0798   0.8324   0.6945
   1.250   0.3358   0.02709   0.01847  -0.0827   0.8291   0.6986
   1.500   0.3555   0.02711   0.01853  -0.0815   0.8199   0.7007
   1.750   0.3901   0.02683   0.01829  -0.0826   0.8155   0.7030
   2.000   0.4136   0.02679   0.01830  -0.0821   0.8066   0.7059
   2.250   0.4487   0.02648   0.01803  -0.0836   0.8014   0.7092
   2.500   0.4771   0.02637   0.01796  -0.0841   0.7929   0.7128
   2.750   0.5110   0.02603   0.01768  -0.0853   0.7869   0.7154
   3.000   0.5352   0.02592   0.01766  -0.0847   0.7776   0.7178
   3.250   0.5683   0.02548   0.01732  -0.0854   0.7715   0.7205
   3.500   0.5932   0.02535   0.01728  -0.0850   0.7607   0.7238
   3.750   0.6308   0.02472   0.01672  -0.0864   0.7551   0.7271
   4.000   0.6569   0.02455   0.01665  -0.0863   0.7424   0.7302
   4.250   0.6818   0.02429   0.01651  -0.0855   0.7297   0.7325
   4.500   0.7095   0.02396   0.01629  -0.0852   0.7168   0.7354
   4.750   0.7400   0.02357   0.01603  -0.0854   0.7029   0.7385
   5.000   0.7730   0.02314   0.01569  -0.0860   0.6871   0.7419
   5.250   0.8100   0.02261   0.01523  -0.0873   0.6687   0.7452
   5.500   0.8481   0.02193   0.01463  -0.0883   0.6469   0.7475
   5.750   0.8863   0.02140   0.01411  -0.0894   0.6172   0.7504
   6.000   0.9228   0.02113   0.01381  -0.0905   0.5803   0.7535
   6.250   0.9567   0.02115   0.01371  -0.0914   0.5401   0.7570
   6.500   0.9846   0.02147   0.01391  -0.0915   0.5002   0.7606
   6.750   1.0052   0.02192   0.01427  -0.0903   0.4635   0.7631
   7.000   1.0233   0.02249   0.01476  -0.0888   0.4281   0.7661
   7.250   1.0400   0.02316   0.01535  -0.0872   0.3925   0.7697
   7.500   1.0559   0.02393   0.01601  -0.0856   0.3565   0.7737
   7.750   1.0699   0.02477   0.01674  -0.0838   0.3212   0.7772
   8.000   1.0815   0.02565   0.01754  -0.0816   0.2867   0.7803
   8.250   1.0931   0.02664   0.01841  -0.0796   0.2494   0.7837
   8.500   1.1038   0.02779   0.01937  -0.0777   0.2113   0.7875
   8.750   1.1143   0.02909   0.02044  -0.0760   0.1688   0.7916
   9.000   1.1232   0.03039   0.02153  -0.0739   0.1309   0.7950
   9.250   1.1338   0.03170   0.02271  -0.0722   0.1018   0.7989
   9.500   1.1450   0.03308   0.02403  -0.0706   0.0778   0.8032
   9.750   1.1545   0.03467   0.02553  -0.0689   0.0582   0.8071
  10.000   1.1616   0.03630   0.02718  -0.0667   0.0460   0.8107
  10.250   1.1676   0.03810   0.02900  -0.0646   0.0389   0.8150
  10.500   1.1752   0.03984   0.03087  -0.0628   0.0341   0.8197
  10.750   1.1800   0.04173   0.03285  -0.0608   0.0312   0.8241
  11.000   1.1862   0.04348   0.03481  -0.0590   0.0288   0.8289
  11.250   1.1918   0.04541   0.03688  -0.0574   0.0272   0.8342
  11.500   1.1947   0.04756   0.03916  -0.0557   0.0261   0.8390
  11.750   1.1972   0.04979   0.04154  -0.0539   0.0253   0.8442
  12.000   1.2023   0.05199   0.04394  -0.0526   0.0245   0.8502
  12.250   1.2064   0.05420   0.04635  -0.0511   0.0238   0.8563
  12.500   1.2110   0.05651   0.04885  -0.0498   0.0231   0.8635
  12.750   1.2151   0.05885   0.05137  -0.0486   0.0226   0.8713
  13.000   1.2189   0.06128   0.05399  -0.0475   0.0220   0.8807
  13.250   1.2209   0.06372   0.05659  -0.0464   0.0214   0.8925
  13.500   1.2212   0.06623   0.05924  -0.0452   0.0209   0.9095
  13.750   1.2179   0.06861   0.06173  -0.0437   0.0205   0.9782
  14.000   1.2214   0.07204   0.06546  -0.0440   0.0199   1.0000
  14.250   1.2228   0.07577   0.06946  -0.0445   0.0194   1.0000
  14.500   1.2218   0.07981   0.07376  -0.0451   0.0191   1.0000
  14.750   1.2187   0.08422   0.07842  -0.0461   0.0188   1.0000
  15.000   1.2132   0.08906   0.08351  -0.0474   0.0186   1.0000
  15.250   1.2052   0.09439   0.08910  -0.0492   0.0185   1.0000
  15.500   1.1948   0.10028   0.09524  -0.0517   0.0184   1.0000
  15.750   1.1820   0.10679   0.10202  -0.0548   0.0184   1.0000
  16.000   1.1669   0.11406   0.10954  -0.0589   0.0184   1.0000
  16.250   1.1493   0.12225   0.11798  -0.0639   0.0185   1.0000
  16.500   1.1290   0.13161   0.12758  -0.0701   0.0186   1.0000
  16.750   1.1055   0.14248   0.13869  -0.0777   0.0188   1.0000
  17.000   1.0770   0.15581   0.15221  -0.0871   0.0192   1.0000
<< Back to EPPLER 403 AIRFOIL (e403-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 403 AIRFOIL (e403-il)