OAF102 AIRFOIL (oaf102-il)
OAF102 AIRFOIL - ONERA/Aerospatiale OAF102 Fenestron airfoil
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(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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Polars for OAF102 AIRFOIL (oaf102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf102-il | 50,000 | 9 | 40.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 5 | 41.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 9 | 61.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 5 | 60.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 9 | 82.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 5 | 77.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 9 | 107.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 5 | 86.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 5 | 92 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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