DORNIER A-5 AIRFOIL (doa5-il)
DORNIER A-5 AIRFOIL - Dornier A-5 airfoil (reconstruction) (DO 228 wing)
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(doa5-il) DORNIER A-5 AIRFOIL Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord. Max camber 2.5% at 76% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DORNIER A-5 AIRFOIL
46. 52.
0.0000000 0.0000000
0.0119800 0.0259000
0.0219600 0.0347300
0.0319400 0.0415200
0.0419200 0.0471100
0.0519000 0.0517000
0.0718600 0.0594800
0.0918200 0.0654700
0.1018000 0.0684400
0.1417200 0.0768500
0.1616800 0.0806400
0.1816400 0.0840300
0.2016000 0.0870300
0.2215600 0.0898200
0.2614800 0.0934100
0.2814400 0.0946100
0.3014000 0.0956100
0.3213600 0.0964100
0.3413200 0.0972100
0.3612800 0.0978000
0.3812400 0.0982000
0.4012000 0.0986000
0.4211600 0.0990000
0.4411200 0.0988000
0.4610800 0.0986000
0.4810400 0.0980000
0.5010000 0.0972100
0.5209600 0.0962100
0.5409200 0.0948100
0.5608800 0.0934100
0.5808400 0.0918200
0.6008000 0.0900200
0.6207600 0.0878200
0.6407200 0.0854300
0.6646701 0.0824300
0.6806400 0.0802400
0.7006000 0.0770500
0.7405200 0.0700600
0.7804400 0.0616800
0.8203600 0.0530900
0.8602800 0.0442200
0.9001999 0.0331300
0.9401200 0.0215600
0.9600800 0.0147700
0.9800400 0.0082800
1.0000000 0.0000000
0.0000000 0.0000000
0.0119800 -.0173700
0.0219600 -.0225600
0.0319400 -.0261500
0.0419200 -.0290200
0.0519000 -.0315400
0.0718600 -.0352500
0.0918200 -.0388000
0.1018000 -.0403200
0.1217600 -.0431100
0.1417200 -.0457100
0.1616800 -.0477100
0.1816400 -.0499000
0.2016000 -.0520900
0.2215600 -.0540900
0.2415200 -.0558900
0.2614800 -.0576800
0.3014000 -.0604800
0.3213600 -.0616800
0.3413200 -.0624700
0.3612800 -.0632700
0.3812400 -.0634700
0.4012000 -.0634700
0.4411200 -.0622700
0.4610800 -.0610800
0.4810400 -.0598800
0.5010000 -.0582800
0.5209600 -.0562900
0.5409200 -.0542900
0.5608800 -.0519000
0.5808400 -.0493000
0.6008000 -.0465100
0.6207600 -.0433100
0.6407200 -.0401200
0.6646701 -.0359300
0.6806400 -.0327300
0.7006000 -.0287400
0.7205999 -.0243500
0.7405200 -.0197600
0.7604800 -.0149700
0.7804400 -.0107800
0.8004000 -.0073800
0.8203600 -.0043900
0.8403200 -.0022000
0.8602800 0.0000000
0.8802400 0.0020000
0.9001999 0.0030000
0.9201500 0.0029000
0.9401200 0.0026000
0.9606000 0.0023000
0.9800400 0.0010000
1.0000000 0.0000000
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Polars for DORNIER A-5 AIRFOIL (doa5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| doa5-il | 50,000 | 9 | 29.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 50,000 | 5 | 25.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 9 | 41.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 5 | 35.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 9 | 52 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 5 | 49.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 9 | 75.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 5 | 59 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 9 | 87.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 5 | 68.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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