DF 101 AIRFOIL (df101-il)
DF 101 AIRFOIL - David Fraser DF 101 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(df101-il) DF 101 AIRFOIL David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord. Max camber 2.3% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DF 101 AIRFOIL
32. 31.
0.0000000 0.0000000
0.0010700 0.0045400
0.0064700 0.0122600
0.0163700 0.0210900
0.0308200 0.0304600
0.0497500 0.0397000
0.0730800 0.0482700
0.1006300 0.0558200
0.1320800 0.0621200
0.1671500 0.0671800
0.2055700 0.0711000
0.2470800 0.0739900
0.2912500 0.0758200
0.3376500 0.0765400
0.3857800 0.0760800
0.4351300 0.0743900
0.4852000 0.0715200
0.5355200 0.0676100
0.5856700 0.0628300
0.6352500 0.0573500
0.6837500 0.0513400
0.7307200 0.0448900
0.7755800 0.0381400
0.8178300 0.0312900
0.8569700 0.0245600
0.8924500 0.0182400
0.9237500 0.0126500
0.9503000 0.0080000
0.9716300 0.0044200
0.9872700 0.0019400
0.9968000 0.0005000
1.0000000 0.0000700
0.0000000 0.0000000
0.0000100 -.0008900
0.0047800 -.0076700
0.0151200 -.0135000
0.0298700 -.0189300
0.0487700 -.0239800
0.0719200 -.0284900
0.0994000 -.0321500
0.1312800 -.0347400
0.1675500 -.0361000
0.2078200 -.0362800
0.2515800 -.0354500
0.2983300 -.0339500
0.3475800 -.0320300
0.3988300 -.0298500
0.4516200 -.0274800
0.5053300 -.0249300
0.5593300 -.0222200
0.6129500 -.0194900
0.6654300 -.0168400
0.7161800 -.0143900
0.7645300 -.0121300
0.8099000 -.0099800
0.8516500 -.0078700
0.8891800 -.0057900
0.9219500 -.0038400
0.9494300 -.0022200
0.9712800 -.0010700
0.9871500 -.0003900
0.9967700 -.0000800
1.0000000 0.0000000
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Polars for DF 101 AIRFOIL (df101-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| df101-il | 50,000 | 9 | 31.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 50,000 | 5 | 34.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 100,000 | 9 | 50.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 100,000 | 5 | 49.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 200,000 | 9 | 68.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 200,000 | 5 | 63 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 500,000 | 9 | 90.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 500,000 | 5 | 80.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 1,000,000 | 9 | 104.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 1,000,000 | 5 | 96.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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