GOE 284 AIRFOIL (goe284-il)
GOE 284 AIRFOIL - Gottingen 284 airfoil
| Details | Dat file | Parser | |
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(goe284-il) GOE 284 AIRFOIL Gottingen 284 airfoil Max thickness 17.7% at 29.3% chord. Max camber 5.1% at 39.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 284 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0108800 0.0317600
0.0227000 0.0450600
0.0466400 0.0657900
0.0708600 0.0810200
0.0952400 0.0931700
0.1441800 0.1138700
0.1935400 0.1264000
0.2929700 0.1373900
0.3930100 0.1366000
0.4937100 0.1229500
0.5947200 0.1033200
0.6958600 0.0808900
0.7971300 0.0560700
0.8985200 0.0288600
0.9492300 0.0150500
1.0000000 0.0029500
0.0000000 0.0000000
0.0137300 -.0240000
0.0266100 -.0315400
0.0520900 -.0408400
0.0772900 -.0446500
0.1023200 -.0453700
0.1523100 -.0451100
0.2022400 -.0437600
0.3019800 -.0386500
0.4017200 -.0335500
0.5014600 -.0284500
0.6012000 -.0233500
0.7009300 -.0182500
0.8006700 -.0131500
0.9004100 -.0080400
0.9502800 -.0054900
1.0000000 -.0029500
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Polars for GOE 284 AIRFOIL (goe284-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe284-il | 50,000 | 9 | 4.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe284-il | 50,000 | 5 | 18 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe284-il | 100,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe284-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe284-il | 200,000 | 9 | 69 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe284-il | 200,000 | 5 | 69.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe284-il | 500,000 | 9 | 103.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe284-il | 500,000 | 5 | 95 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe284-il | 1,000,000 | 9 | 126.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe284-il | 1,000,000 | 5 | 107.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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