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OAF128 AIRFOIL (oaf128-il)

OAF128 AIRFOIL - ONERA/Aerospatiale OAF128 Fenestron airfoil


Airfoil oaf128-il
Details Dat file Parser  
(oaf128-il) OAF128 AIRFOIL
ONERA/Aerospatiale OAF128 Fenestron airfoil
Max thickness 12.8% at 23.2% chord.
Max camber 1% at 43.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
OAF128 AIRFOIL
      51.0      51.0
 
 0.0000000 0.0000000
 0.0009870 0.0063720
 0.0039430 0.0130080
 0.0088560 0.0197420
 0.0157080 0.0263590
 0.0244720 0.0326580
 0.0351120 0.0385040
 0.0475860 0.0438610
 0.0618470 0.0487680
 0.0778360 0.0533000
 0.0954920 0.0574980
 0.1147430 0.0613280
 0.1355160 0.0646740
 0.1577260 0.0673980
 0.1812880 0.0694360
 0.2061070 0.0708680
 0.2320870 0.0718550
 0.2591230 0.0722570
 0.2871100 0.0719690
 0.3159380 0.0711220
 0.3454920 0.0697220
 0.3756550 0.0678290
 0.4063090 0.0655120
 0.4373330 0.0628440
 0.4686050 0.0598940
 0.5000000 0.0567290
 0.5313950 0.0534080
 0.5626670 0.0499820
 0.5936910 0.0464950
 0.6243450 0.0429840
 0.6545080 0.0394830
 0.6840620 0.0360200
 0.7128900 0.0326230
 0.7408770 0.0293200
 0.7679130 0.0261400
 0.7938930 0.0231130
 0.8187120 0.0202680
 0.8422740 0.0176370
 0.8644840 0.0152430
 0.8852570 0.0131090
 0.9045080 0.0112480
 0.9221640 0.0096650
 0.9381530 0.0083560
 0.9524140 0.0073050
 0.9648880 0.0064910
 0.9755280 0.0058840
 0.9842920 0.0054500
 0.9911440 0.0051560
 0.9960570 0.0049710
 0.9990130 0.0048710
 1.0000000 0.0048390
 
 0.0000000 0.0000000
 0.0009870 -.0073700
 0.0039430 -.0136370
 0.0088560 -.0190730
 0.0157080 -.0240160
 0.0244720 -.0287360
 0.0351120 -.0333460
 0.0475860 -.0377820
 0.0618470 -.0418710
 0.0778360 -.0454500
 0.0954920 -.0484680
 0.1147430 -.0509930
 0.1355160 -.0530960
 0.1577260 -.0546830
 0.1812880 -.0555200
 0.2061070 -.0558650
 0.2320870 -.0560020
 0.2591230 -.0554310
 0.2871100 -.0543230
 0.3159380 -.0527340
 0.3454920 -.0507300
 0.3756550 -.0483880
 0.4063090 -.0457880
 0.4373330 -.0430040
 0.4686050 -.0401080
 0.5000000 -.0371590
 0.5313950 -.0342100
 0.5626670 -.0312970
 0.5936910 -.0284510
 0.6243450 -.0256930
 0.6545080 -.0230380
 0.6840620 -.0204990
 0.7128900 -.0180890
 0.7408770 -.0158230
 0.7679130 -.0137170
 0.7938930 -.0117910
 0.8187120 -.0100670
 0.8422740 -.0085640
 0.8644840 -.0073010
 0.8852570 -.0062890
 0.9045080 -.0055320
 0.9221640 -.0050210
 0.9381530 -.0047390
 0.9524140 -.0046540
 0.9648880 -.0047270
 0.9755280 -.0049100
 0.9842920 -.0051520
 0.9911440 -.0054030
 0.9960570 -.0056190
 0.9990130 -.0057630
 1.0000000 -.0058140
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Lednicer format dat file
Selig format dat file

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Polars for OAF128 AIRFOIL (oaf128-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   oaf128-il50,000924.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf128-il50,000531.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf128-il100,000941.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf128-il100,000543.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf128-il200,000956.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf128-il200,000555.5 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf128-il500,000974.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf128-il500,000571 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   oaf128-il1,000,000985.4 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   oaf128-il1,000,000585.2 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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