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DORNIER A-5 AIRFOIL (doa5-il)

DORNIER A-5 AIRFOIL - Dornier A-5 airfoil (reconstruction) (DO 228 wing)


Airfoil doa5-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   doa5-il50,000929.9 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   doa5-il50,000525.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   doa5-il100,000941.3 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   doa5-il100,000535.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   doa5-il200,000952 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   doa5-il200,000549.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   doa5-il500,000975.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   doa5-il500,000559 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
   doa5-il1,000,000987.6 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   doa5-il1,000,000568.7 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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