OAF095 AIRFOIL (oaf095-il)
OAF095 AIRFOIL - ONERA/Aerospatiale OAF095 Fenestron airfoil
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(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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Polars for OAF095 AIRFOIL (oaf095-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf095-il | 50,000 | 9 | 43.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 5 | 43.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 9 | 65.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 5 | 63.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 9 | 88.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 5 | 82.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 9 | 116.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 5 | 93.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 5 | 98.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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