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OAF095 AIRFOIL (oaf095-il)

OAF095 AIRFOIL - ONERA/Aerospatiale OAF095 Fenestron airfoil


Airfoil oaf095-il
Details Dat file Parser  
(oaf095-il) OAF095 AIRFOIL
ONERA/Aerospatiale OAF095 Fenestron airfoil
Max thickness 9.5% at 23.2% chord.
Max camber 3.9% at 53.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
OAF095 AIRFOIL
      51.0      51.0
 
 0.0000000 0.0000000
 0.0009870 0.0050860
 0.0039430 0.0101450
 0.0088560 0.0151760
 0.0157080 0.0201780
 0.0244720 0.0251450
 0.0351120 0.0300660
 0.0475860 0.0349210
 0.0618470 0.0396830
 0.0778360 0.0443160
 0.0954920 0.0487820
 0.1147430 0.0530390
 0.1355160 0.0570540
 0.1577260 0.0607950
 0.1812880 0.0642360
 0.2061070 0.0673560
 0.2320870 0.0701270
 0.2591230 0.0725180
 0.2871100 0.0744860
 0.3159380 0.0759890
 0.3454920 0.0769970
 0.3756550 0.0775270
 0.4063090 0.0774670
 0.4373330 0.0767050
 0.4686050 0.0754860
 0.5000000 0.0737740
 0.5313950 0.0715720
 0.5626670 0.0689110
 0.5936910 0.0658400
 0.6243450 0.0624140
 0.6545080 0.0586910
 0.6840620 0.0547270
 0.7128900 0.0505740
 0.7408770 0.0462840
 0.7679130 0.0419080
 0.7938930 0.0374990
 0.8187120 0.0331140
 0.8422740 0.0288130
 0.8644840 0.0246600
 0.8852570 0.0207170
 0.9045080 0.0170420
 0.9221640 0.0136870
 0.9381530 0.0106910
 0.9524140 0.0080810
 0.9648880 0.0058660
 0.9755280 0.0040430
 0.9842920 0.0025990
 0.9911440 0.0015120
 0.9960570 0.0007580
 0.9990130 0.0003150
 1.0000000 0.0001690
 
 0.0000000 0.0000000
 0.0009870 -.0043830
 0.0039430 -.0086980
 0.0088560 -.0128110
 0.0157080 -.0165900
 0.0244720 -.0199650
 0.0351120 -.0229270
 0.0475860 -.0254680
 0.0618470 -.0275250
 0.0778360 -.0290180
 0.0954920 -.0299670
 0.1147430 -.0304010
 0.1355160 -.0302550
 0.1577260 -.0294740
 0.1812880 -.0282800
 0.2061070 -.0266640
 0.2320870 -.0246400
 0.2591230 -.0222400
 0.2871100 -.0195180
 0.3159380 -.0165440
 0.3454920 -.0133980
 0.3756550 -.0101710
 0.4063090 -.0069540
 0.4373330 -.0038330
 0.4686050 -.0008870
 0.5000000 0.0018180
 0.5313950 0.0042310
 0.5626670 0.0063190
 0.5936910 0.0080620
 0.6243450 0.0094570
 0.6545080 0.0105110
 0.6840620 0.0112400
 0.7128900 0.0116620
 0.7408770 0.0118000
 0.7679130 0.0116740
 0.7938930 0.0113030
 0.8187120 0.0107040
 0.8422740 0.0098930
 0.8644840 0.0088860
 0.8852570 0.0077020
 0.9045080 0.0063680
 0.9221640 0.0049160
 0.9381530 0.0033850
 0.9524140 0.0018270
 0.9648880 0.0002970
 0.9755280 -.0011420
 0.9842920 -.0024290
 0.9911440 -.0035020
 0.9960570 -.0043110
 0.9990130 -.0048140
 1.0000000 -.0049840
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Lednicer format dat file
Selig format dat file

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Polars for OAF095 AIRFOIL (oaf095-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oaf095-il50,000943.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf095-il50,000543.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf095-il100,000965.7 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf095-il100,000563.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf095-il200,000988.2 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf095-il200,000582.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf095-il500,0009116.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf095-il500,000593.2 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf095-il1,000,0009131.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf095-il1,000,000598.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
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