GOE 546 AIRFOIL (goe546-il)
GOE 546 AIRFOIL - Gottingen 546 airfoil
| Details | Dat file | Parser | |
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(goe546-il) GOE 546 AIRFOIL Gottingen 546 airfoil Max thickness 10.4% at 30% chord. Max camber 3.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 546 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0208600
0.0250000 0.0282200
0.0500000 0.0399500
0.0750000 0.0486700
0.1000000 0.0559000
0.1500000 0.0673500
0.2000000 0.0748000
0.3000000 0.0837000
0.4000000 0.0851000
0.5000000 0.0810000
0.6000000 0.0717000
0.7000000 0.0593000
0.8000000 0.0422000
0.9000000 0.0226000
0.9500000 0.0125500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0116400
0.0250000 -.0152800
0.0500000 -.0185500
0.0750000 -.0203300
0.1000000 -.0216000
0.1500000 -.0229500
0.2000000 -.0232000
0.3000000 -.0203000
0.4000000 -.0154000
0.5000000 -.0095000
0.6000000 -.0046000
0.7000000 -.0012000
0.8000000 0.0007000
0.9000000 0.0016000
0.9500000 0.0010500
1.0000000 0.0000000
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Polars for GOE 546 AIRFOIL (goe546-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe546-il | 50,000 | 9 | 38.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe546-il | 50,000 | 5 | 38.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe546-il | 100,000 | 9 | 59.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe546-il | 100,000 | 5 | 58.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe546-il | 200,000 | 9 | 80.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe546-il | 200,000 | 5 | 76.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe546-il | 500,000 | 9 | 106.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe546-il | 500,000 | 5 | 93.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe546-il | 1,000,000 | 9 | 124.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe546-il | 1,000,000 | 5 | 101.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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