OAF139 AIRFOIL (oaf139-il)
OAF139 AIRFOIL - ONERA/Aerospatiale OAF139 Fenestron airfoil
| Details | Dat file | Parser | |
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(oaf139-il) OAF139 AIRFOIL ONERA/Aerospatiale OAF139 Fenestron airfoil Max thickness 13.7% at 23.2% chord. Max camber 0% at 0.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
OAF139 AIRFOIL
51.0 51.0
0.0000000 0.0000000
0.0009870 0.0069740
0.0039430 0.0135150
0.0088560 0.0196740
0.0157080 0.0255040
0.0244720 0.0310280
0.0351120 0.0362150
0.0475860 0.0409900
0.0618470 0.0452640
0.0778360 0.0489770
0.0954920 0.0521160
0.1147430 0.0547010
0.1355160 0.0567240
0.1577260 0.0581040
0.1812880 0.0587940
0.2061070 0.0589760
0.2320870 0.0586210
0.2591230 0.0576860
0.2871100 0.0562060
0.3159380 0.0542310
0.3454920 0.0518300
0.3756550 0.0490790
0.4063090 0.0460610
0.4373330 0.0428590
0.4686050 0.0395500
0.5000000 0.0362080
0.5313950 0.0328930
0.5626670 0.0296580
0.5936910 0.0265420
0.6243450 0.0235750
0.6545080 0.0207810
0.6840620 0.0181750
0.7128900 0.0157690
0.7408770 0.0135700
0.7679130 0.0115880
0.7938930 0.0098290
0.8187120 0.0083000
0.8422740 0.0070050
0.8644840 0.0059460
0.8852570 0.0051220
0.9045080 0.0045240
0.9221640 0.0041380
0.9381530 0.0039400
0.9524140 0.0039010
0.9648880 0.0039860
0.9755280 0.0041540
0.9842920 0.0043650
0.9911440 0.0045780
0.9960570 0.0047580
0.9990130 0.0048780
1.0000000 0.0049200
0.0000000 0.0000000
0.0009870 -.0062800
0.0039430 -.0129290
0.0088560 -.0198060
0.0157080 -.0267190
0.0244720 -.0334750
0.0351120 -.0399250
0.0475860 -.0459840
0.0618470 -.0516240
0.0778360 -.0568500
0.0954920 -.0616510
0.1147430 -.0659750
0.1355160 -.0697270
0.1577260 -.0728090
0.1812880 -.0751830
0.2061070 -.0769130
0.2320870 -.0780940
0.2591230 -.0785610
0.2871100 -.0782850
0.3159380 -.0774410
0.3454920 -.0760120
0.3756550 -.0740480
0.4063090 -.0716090
0.4373330 -.0687660
0.4686050 -.0655950
0.5000000 -.0621690
0.5313950 -.0585600
0.5626670 -.0548320
0.5936910 -.0510420
0.6243450 -.0472380
0.6545080 -.0434590
0.6840620 -.0397410
0.7128900 -.0361120
0.7408770 -.0325980
0.7679130 -.0292240
0.7938930 -.0260110
0.8187120 -.0229840
0.8422740 -.0201650
0.8644840 -.0175730
0.8852570 -.0152250
0.9045080 -.0131340
0.9221640 -.0113070
0.9381530 -.0097430
0.9524140 -.0084340
0.9648880 -.0073660
0.9755280 -.0065190
0.9842920 -.0058720
0.9911440 -.0054000
0.9960570 -.0050810
0.9990130 -.0048970
1.0000000 -.0048370
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Polars for OAF139 AIRFOIL (oaf139-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf139-il | 50,000 | 9 | 13.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 50,000 | 5 | 20.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 100,000 | 9 | 26.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 100,000 | 5 | 31.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 200,000 | 9 | 39.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 200,000 | 5 | 43.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 500,000 | 9 | 58.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 500,000 | 5 | 59.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 1,000,000 | 9 | 73.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 1,000,000 | 5 | 72.3 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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