OAF128 AIRFOIL (oaf128-il)
OAF128 AIRFOIL - ONERA/Aerospatiale OAF128 Fenestron airfoil
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(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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Polars for OAF128 AIRFOIL (oaf128-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf128-il | 50,000 | 9 | 24.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 50,000 | 5 | 31.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 9 | 41.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 5 | 43.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 9 | 56.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 5 | 55.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 9 | 74.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 5 | 71 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 9 | 85.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 5 | 85.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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