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OAF117 AIRFOIL (oaf117-il)

OAF117 AIRFOIL - ONERA/Aerospatiale OAF117 Fenestron airfoil


Airfoil oaf117-il
Details Dat file Parser  
(oaf117-il) OAF117 AIRFOIL
ONERA/Aerospatiale OAF117 Fenestron airfoil
Max thickness 11.5% at 23.2% chord.
Max camber 2% at 46.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
OAF117 AIRFOIL
      51.0      51.0
 
 0.0000000 0.0000000
 0.0009870 0.0066160
 0.0039430 0.0129130
 0.0088560 0.0189500
 0.0157080 0.0248040
 0.0244720 0.0305360
 0.0351120 0.0361690
 0.0475860 0.0416720
 0.0618470 0.0469650
 0.0778360 0.0519450
 0.0954920 0.0565120
 0.1147430 0.0606020
 0.1355160 0.0641960
 0.1577260 0.0672970
 0.1812880 0.0698950
 0.2061070 0.0719280
 0.2320870 0.0732880
 0.2591230 0.0739400
 0.2871100 0.0741820
 0.3159380 0.0737510
 0.3454920 0.0727790
 0.3756550 0.0712980
 0.4063090 0.0693530
 0.4373330 0.0669990
 0.4686050 0.0642960
 0.5000000 0.0613050
 0.5313950 0.0580870
 0.5626670 0.0547000
 0.5936910 0.0511980
 0.6243450 0.0476280
 0.6545080 0.0440330
 0.6840620 0.0404510
 0.7128900 0.0369170
 0.7408770 0.0334620
 0.7679130 0.0301180
 0.7938930 0.0269110
 0.8187120 0.0238710
 0.8422740 0.0210220
 0.8644840 0.0183870
 0.8852570 0.0159860
 0.9045080 0.0138320
 0.9221640 0.0119330
 0.9381530 0.0102920
 0.9524140 0.0089020
 0.9648880 0.0077530
 0.9755280 0.0068290
 0.9842920 0.0061110
 0.9911440 0.0055780
 0.9960570 0.0052130
 0.9990130 0.0050010
 1.0000000 0.0049310
 
 0.0000000 0.0000000
 0.0009870 -.0052160
 0.0039430 -.0104160
 0.0088560 -.0154420
 0.0157080 -.0201210
 0.0244720 -.0243480
 0.0351120 -.0281210
 0.0475860 -.0315040
 0.0618470 -.0345470
 0.0778360 -.0372010
 0.0954920 -.0393320
 0.1147430 -.0408480
 0.1355160 -.0418560
 0.1577260 -.0425490
 0.1812880 -.0425030
 0.2061070 -.0421770
 0.2320870 -.0413890
 0.2591230 -.0401610
 0.2871100 -.0385330
 0.3159380 -.0365570
 0.3454920 -.0342970
 0.3756550 -.0318210
 0.4063090 -.0291990
 0.4373330 -.0265000
 0.4686050 -.0237870
 0.5000000 -.0211170
 0.5313950 -.0185370
 0.5626670 -.0160860
 0.5936910 -.0137910
 0.6243450 -.0116740
 0.6545080 -.0097490
 0.6840620 -.0080230
 0.7128900 -.0065020
 0.7408770 -.0051890
 0.7679130 -.0040830
 0.7938930 -.0031840
 0.8187120 -.0024920
 0.8422740 -.0020010
 0.8644840 -.0017060
 0.8852570 -.0015970
 0.9045080 -.0016570
 0.9221640 -.0018650
 0.9381530 -.0021960
 0.9524140 -.0026170
 0.9648880 -.0030920
 0.9755280 -.0035830
 0.9842920 -.0040500
 0.9911440 -.0044580
 0.9960570 -.0047740
 0.9990130 -.0049740
 1.0000000 -.0050420
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Lednicer format dat file
Selig format dat file

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Polars for OAF117 AIRFOIL (oaf117-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oaf117-il50,000928.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf117-il50,000534.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf117-il100,000946.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf117-il100,000549.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf117-il200,000964.2 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf117-il200,000563 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf117-il500,000984.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf117-il500,000578.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf117-il1,000,000996.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf117-il1,000,000589.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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