EPPLER 335 AIRFOIL (e335-il)
EPPLER 335 AIRFOIL - Eppler E335 flying wing airfoil
| Details | Dat file | Parser | |
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(e335-il) EPPLER 335 AIRFOIL Eppler E335 flying wing airfoil Max thickness 12.6% at 29% chord. Max camber 2.3% at 19.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 335 AIRFOIL
34. 39.
0.0000100 0.0002400
0.0001200 0.0017100
0.0006300 0.0040600
0.0010200 0.0053000
0.0061200 0.0144100
0.0153800 0.0243300
0.0286700 0.0345000
0.0459000 0.0445200
0.0669400 0.0540700
0.0915900 0.0628400
0.1196700 0.0705400
0.1509500 0.0768700
0.1852200 0.0815400
0.2223800 0.0842900
0.2623300 0.0849700
0.3050900 0.0835300
0.3505600 0.0802900
0.3983700 0.0755600
0.4480900 0.0696200
0.4992500 0.0627900
0.5512900 0.0553800
0.6035900 0.0477200
0.6554800 0.0401300
0.7062400 0.0328800
0.7551100 0.0262000
0.8013300 0.0202700
0.8441500 0.0152000
0.8828501 0.0110200
0.9167401 0.0076900
0.9452500 0.0050200
0.9681000 0.0027400
0.9852600 0.0009900
0.9962000 0.0001500
1.0000000 0.0000000
0.0000100 0.0002400
0.0000600 -.0011400
0.0001700 -.0017800
0.0003300 -.0023900
0.0005600 -.0029400
0.0008800 -.0034600
0.0013100 -.0039700
0.0018200 -.0044800
0.0030600 -.0054900
0.0045800 -.0064900
0.0073300 -.0079900
0.0179500 -.0121700
0.0356300 -.0168100
0.0586900 -.0210500
0.0868900 -.0249200
0.1199500 -.0285200
0.1574000 -.0319900
0.1986400 -.0353800
0.2430500 -.0386000
0.2900400 -.0415600
0.3390400 -.0441100
0.3895300 -.0461500
0.4409800 -.0476200
0.4928200 -.0484800
0.5445100 -.0486900
0.5954800 -.0482200
0.6451800 -.0470700
0.6930800 -.0452000
0.7386500 -.0426100
0.7813800 -.0392500
0.8207901 -.0349400
0.8568400 -.0293400
0.8899900 -.0227400
0.9201500 -.0161600
0.9465700 -.0103000
0.9685400 -.0055300
0.9854000 -.0021700
0.9962300 -.0004500
1.0000000 0.0000000
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Polars for EPPLER 335 AIRFOIL (e335-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e335-il | 50,000 | 9 | 15.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 50,000 | 5 | 25.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 100,000 | 9 | 38.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 100,000 | 5 | 44.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 200,000 | 9 | 60.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 200,000 | 5 | 58.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 500,000 | 9 | 81.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 500,000 | 5 | 72 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 9 | 90.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e335-il | 1,000,000 | 5 | 88.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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