OAF117 AIRFOIL (oaf117-il)
OAF117 AIRFOIL - ONERA/Aerospatiale OAF117 Fenestron airfoil
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(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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Polars for OAF117 AIRFOIL (oaf117-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf117-il | 50,000 | 9 | 28.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 9 | 46.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 100,000 | 5 | 49.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 9 | 64.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 200,000 | 5 | 63 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 9 | 96.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf117-il | 1,000,000 | 5 | 89.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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