EPPLER 551 AIRFOIL (e551-il)
EPPLER 551 AIRFOIL - Eppler E551 general aviation airfoil
| Details | Dat file | Parser | |
|
(e551-il) EPPLER 551 AIRFOIL Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord. Max camber 2.8% at 57.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 551 AIRFOIL
35. 38.
0.0000100 0.0005200
0.0002000 0.0022500
0.0005900 0.0040800
0.0015500 0.0069800
0.0048800 0.0133800
0.0138900 0.0244600
0.0272400 0.0360300
0.0447800 0.0477100
0.0663500 0.0591500
0.0917600 0.0700900
0.1207700 0.0802900
0.1531100 0.0895500
0.1884700 0.0976600
0.2265000 0.1044600
0.2668200 0.1097700
0.3090100 0.1133800
0.3527500 0.1150300
0.3978400 0.1145100
0.4442000 0.1118300
0.4916200 0.1072500
0.5397100 0.1010200
0.5880600 0.0934100
0.6362200 0.0847100
0.6837100 0.0752300
0.7300100 0.0653000
0.7745600 0.0552800
0.8167700 0.0455000
0.8560200 0.0362600
0.8916600 0.0278300
0.9230400 0.0203800
0.9495700 0.0140300
0.9706600 0.0087000
0.9862200 0.0041800
0.9963400 0.0010600
1.0000000 0.0000000
0.0000100 0.0005200
0.0000100 -.0003100
0.0000600 -.0010900
0.0002000 -.0018400
0.0004400 -.0025600
0.0007800 -.0033000
0.0012000 -.0040400
0.0022400 -.0055600
0.0035500 -.0071000
0.0059400 -.0094700
0.0096900 -.0125200
0.0231500 -.0206300
0.0416000 -.0286400
0.0647000 -.0363300
0.0921600 -.0435500
0.1236100 -.0501800
0.1586300 -.0560800
0.1967100 -.0611000
0.2373800 -.0650100
0.2801100 -.0675900
0.3243400 -.0683600
0.3700000 -.0667100
0.4174300 -.0624600
0.4669000 -.0560200
0.5182700 -.0482100
0.5709400 -.0397500
0.6241800 -.0311800
0.6771801 -.0230100
0.7290800 -.0156400
0.7789400 -.0093900
0.8258100 -.0044800
0.8687200 -.0010100
0.9067800 0.0010800
0.9391500 0.0019500
0.9651600 0.0019200
0.9842900 0.0012800
0.9960400 0.0004300
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for EPPLER 551 AIRFOIL (e551-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e551-il | 50,000 | 9 | 4.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 50,000 | 5 | 14.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 100,000 | 9 | 43.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 100,000 | 5 | 47.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 200,000 | 9 | 72.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 200,000 | 5 | 70 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 500,000 | 9 | 102.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 500,000 | 5 | 95.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 9 | 125.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e551-il | 1,000,000 | 5 | 113.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||