EPPLER 561 AIRFOIL (e561-il)
EPPLER 561 AIRFOIL - Eppler E561 general aviation airfoil
| Details | Dat file | Parser | |
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(e561-il) EPPLER 561 AIRFOIL Eppler E561 general aviation airfoil Max thickness 16.9% at 27.9% chord. Max camber 5.1% at 45.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 561 AIRFOIL
33. 29.
0.0000200 0.0009200
0.0033000 0.0121300
0.0107700 0.0247100
0.0222400 0.0379600
0.0376300 0.0514400
0.0567800 0.0647800
0.0795300 0.0776300
0.1056600 0.0896900
0.1349300 0.1006400
0.1671300 0.1101700
0.2020400 0.1180000
0.2394400 0.1239000
0.2791500 0.1276700
0.3210000 0.1291800
0.3649200 0.1284400
0.4106900 0.1256800
0.4579300 0.1211700
0.5061900 0.1151100
0.5550300 0.1077600
0.6039200 0.0993800
0.6523400 0.0902400
0.6997100 0.0806100
0.7454600 0.0707600
0.7889900 0.0609400
0.8297000 0.0513700
0.8670099 0.0422300
0.9003700 0.0336500
0.9292800 0.0257400
0.9532400 0.0184300
0.9722300 0.0114900
0.9867401 0.0053700
0.9964600 0.0013300
1.0000000 0.0000000
0.0000200 0.0009200
0.0022700 -.0082700
0.0106700 -.0164100
0.0242600 -.0243700
0.0424700 -.0316800
0.0650100 -.0379700
0.0916800 -.0429000
0.1223300 -.0462300
0.1568300 -.0477300
0.1951200 -.0473300
0.2370600 -.0450400
0.2825000 -.0409900
0.3312700 -.0353800
0.3832000 -.0286400
0.4378200 -.0214600
0.4942900 -.0143700
0.5517400 -.0077500
0.6092600 -.0018700
0.6659600 0.0030400
0.7209100 0.0068500
0.7732200 0.0094400
0.8219900 0.0108100
0.8663900 0.0109800
0.9056200 0.0100500
0.9389300 0.0081700
0.9655200 0.0055900
0.9847000 0.0028800
0.9961900 0.0007900
1.0000000 0.0000000
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Polars for EPPLER 561 AIRFOIL (e561-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e561-il | 50,000 | 9 | 5.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 50,000 | 5 | 26.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 100,000 | 9 | 39.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 100,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 200,000 | 9 | 70 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 200,000 | 5 | 74.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 500,000 | 9 | 105 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 500,000 | 5 | 104.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 1,000,000 | 9 | 134.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 1,000,000 | 5 | 128.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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