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OAF102 AIRFOIL (oaf102-il)

OAF102 AIRFOIL - ONERA/Aerospatiale OAF102 Fenestron airfoil


Airfoil oaf102-il
Details Dat file Parser  
(oaf102-il) OAF102 AIRFOIL
ONERA/Aerospatiale OAF102 Fenestron airfoil
Max thickness 10.2% at 28.7% chord.
Max camber 3.6% at 53.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
OAF102 AIRFOIL
      51.0      51.0
 
 0.0000000 0.0000000
 0.0009870 0.0046060
 0.0039430 0.0092000
 0.0088560 0.0137910
 0.0157080 0.0183940
 0.0244720 0.0230230
 0.0351120 0.0276870
 0.0475860 0.0323860
 0.0618470 0.0371040
 0.0778360 0.0418150
 0.0954920 0.0464800
 0.1147430 0.0510510
 0.1355160 0.0554790
 0.1577260 0.0597120
 0.1812880 0.0636970
 0.2061070 0.0673850
 0.2320870 0.0707200
 0.2591230 0.0736410
 0.2871100 0.0760840
 0.3159380 0.0779820
 0.3454920 0.0792870
 0.3756550 0.0799960
 0.4063090 0.0801020
 0.4373330 0.0794940
 0.4686050 0.0783960
 0.5000000 0.0767060
 0.5313950 0.0744090
 0.5626670 0.0715490
 0.5936910 0.0682100
 0.6243450 0.0644940
 0.6545080 0.0605020
 0.6840620 0.0563260
 0.7128900 0.0520440
 0.7408770 0.0477170
 0.7679130 0.0433970
 0.7938930 0.0391240
 0.8187120 0.0349420
 0.8422740 0.0308900
 0.8644840 0.0270150
 0.8852570 0.0233640
 0.9045080 0.0199840
 0.9221640 0.0169170
 0.9381530 0.0141980
 0.9524140 0.0118480
 0.9648880 0.0098730
 0.9755280 0.0082680
 0.9842920 0.0070130
 0.9911440 0.0060810
 0.9960570 0.0054430
 0.9990130 0.0050720
 1.0000000 0.0049500
 
 0.0000000 0.0000000
 0.0009870 -.0041390
 0.0039430 -.0081810
 0.0088560 -.0120750
 0.0157080 -.0157610
 0.0244720 -.0191910
 0.0351120 -.0223310
 0.0475860 -.0251540
 0.0618470 -.0276150
 0.0778360 -.0296520
 0.0954920 -.0312080
 0.1147430 -.0322730
 0.1355160 -.0328460
 0.1577260 -.0328980
 0.1812880 -.0322540
 0.2061070 -.0312240
 0.2320870 -.0297750
 0.2591230 -.0279010
 0.2871100 -.0256230
 0.3159380 -.0229870
 0.3454920 -.0200630
 0.3756550 -.0169400
 0.4063090 -.0137190
 0.4373330 -.0105030
 0.4686050 -.0073910
 0.5000000 -.0044730
 0.5313950 -.0018180
 0.5626670 0.0005240
 0.5936910 0.0025230
 0.6243450 0.0041710
 0.6545080 0.0054770
 0.6840620 0.0064610
 0.7128900 0.0071510
 0.7408770 0.0075760
 0.7679130 0.0077630
 0.7938930 0.0077330
 0.8187120 0.0075010
 0.8422740 0.0070770
 0.8644840 0.0064660
 0.8852570 0.0056770
 0.9045080 0.0047190
 0.9221640 0.0036140
 0.9381530 0.0023910
 0.9524140 0.0010920
 0.9648880 -.0002280
 0.9755280 -.0015070
 0.9842920 -.0026760
 0.9911440 -.0036710
 0.9960570 -.0044300
 0.9990130 -.0049060
 1.0000000 -.0050680
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Lednicer format dat file
Selig format dat file

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Polars for OAF102 AIRFOIL (oaf102-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oaf102-il50,000940.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf102-il50,000541.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf102-il100,000961.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf102-il100,000560.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf102-il200,000982.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf102-il200,000577.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf102-il500,0009107.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf102-il500,000586.3 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf102-il1,000,0009114 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf102-il1,000,000592 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
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