GOE 701 AIRFOIL (goe701-il)
GOE 701 AIRFOIL - Gottingen 701 airfoil
| Details | Dat file | Parser | |
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(goe701-il) GOE 701 AIRFOIL Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord. Max camber 4.9% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 701 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0116900 0.0239000
0.0238200 0.0348100
0.0481900 0.0531400
0.0727600 0.0659700
0.0974200 0.0758100
0.1469200 0.0897100
0.1966600 0.0981900
0.2963400 0.1075800
0.3963000 0.1089700
0.4964900 0.1033800
0.5968800 0.0917900
0.6974600 0.0747100
0.7981800 0.0536400
0.8990100 0.0290700
0.9495000 0.0147800
1.0000000 0.0000000
0.0000000 0.0000000
0.0130600 -.0165600
0.0257900 -.0231200
0.0509800 -.0287700
0.0760500 -.0309100
0.1010400 -.0305600
0.1509500 -.0278700
0.2008100 -.0236700
0.3005700 -.0167800
0.4003900 -.0113900
0.5002900 -.0084900
0.6002200 -.0065900
0.7002100 -.0061900
0.8001800 -.0052900
0.9001200 -.0034000
0.9500600 -.0017000
1.0000000 0.0000000
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Polars for GOE 701 AIRFOIL (goe701-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe701-il | 50,000 | 9 | 19.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 50,000 | 5 | 31.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 100,000 | 9 | 54.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 100,000 | 5 | 53.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 200,000 | 9 | 78.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 200,000 | 5 | 73.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 500,000 | 9 | 108.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 500,000 | 5 | 94.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe701-il | 1,000,000 | 9 | 127.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe701-il | 1,000,000 | 5 | 101.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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