EPPLER 562 AIRFOIL (e562-il)
EPPLER 562 AIRFOIL - Eppler E562 general aviation airfoil
| Details | Dat file | Parser | |
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(e562-il) EPPLER 562 AIRFOIL Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord. Max camber 4% at 50.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 562 AIRFOIL
33. 29.
0.0002300 -.0023100
0.0015700 0.0063800
0.0076600 0.0167800
0.0180400 0.0279800
0.0325400 0.0395000
0.0510300 0.0509400
0.0733400 0.0620000
0.0992800 0.0723800
0.1286200 0.0818100
0.1611300 0.0900000
0.1966200 0.0967100
0.2348700 0.1017900
0.2756700 0.1051000
0.3188000 0.1066200
0.3640000 0.1064000
0.4109400 0.1045800
0.4591800 0.1013100
0.5082800 0.0967600
0.5577500 0.0911100
0.6070700 0.0845600
0.6557100 0.0773200
0.7031200 0.0696000
0.7487200 0.0616000
0.7919500 0.0535200
0.8322600 0.0455300
0.8691000 0.0378000
0.9019700 0.0304200
0.9304100 0.0235000
0.9539700 0.0169800
0.9726600 0.0106500
0.9869500 0.0049900
0.9965200 0.0012300
1.0000000 0.0000000
0.0002300 -.0023100
0.0049200 -.0099100
0.0155400 -.0175400
0.0309900 -.0249200
0.0509900 -.0316900
0.0753000 -.0376100
0.1036300 -.0423400
0.1357800 -.0459000
0.1715400 -.0478500
0.2107400 -.0481100
0.2532200 -.0466600
0.2987900 -.0435800
0.3472100 -.0390100
0.3982100 -.0331800
0.4515200 -.0265100
0.5066000 -.0196200
0.5626200 -.0129900
0.6187000 -.0069300
0.6739600 -.0016900
0.7275200 0.0025400
0.7785100 0.0056500
0.8260700 0.0076000
0.8693700 0.0083800
0.9076500 0.0080700
0.9401700 0.0068000
0.9661600 0.0047700
0.9849600 0.0025000
0.9962400 0.0007000
1.0000000 0.0000000
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Polars for EPPLER 562 AIRFOIL (e562-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e562-il | 50,000 | 9 | 11.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 50,000 | 5 | 33.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 100,000 | 9 | 49.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 100,000 | 5 | 55.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 200,000 | 9 | 73.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 500,000 | 9 | 104.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 500,000 | 5 | 100.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 9 | 129.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 5 | 115.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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