GOE 331 (PFALZ 60) AIRFOIL (goe331-il)
GOE 331 (PFALZ 60) AIRFOIL - Gottingen 331 (Pfalz 60) airfoil
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(goe331-il) GOE 331 (PFALZ 60) AIRFOIL Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord. Max camber 6.9% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 331 (PFALZ 60) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122100 0.0301200
0.0245900 0.0424400
0.0494100 0.0612800
0.0742600 0.0758200
0.0991600 0.0869600
0.1489900 0.1037500
0.1989000 0.1137300
0.2988200 0.1212000
0.3988200 0.1215700
0.4988900 0.1145400
0.5990200 0.1012100
0.6992100 0.0815800
0.7994400 0.0579500
0.8996900 0.0322300
0.9498400 0.0168100
1.0000000 0.0013000
0.0000000 0.0000000
0.0126100 -.0108800
0.0250800 -.0086600
0.0500400 -.0041100
0.0750000 -.0001700
0.0999700 0.0029700
0.1499200 0.0080500
0.1998900 0.0114400
0.2998600 0.0148100
0.3998500 0.0157800
0.4998500 0.0151500
0.5998700 0.0134200
0.6999000 0.0101900
0.7999300 0.0068600
0.8999700 0.0030300
0.9499900 0.0009100
1.0000000 -.0013000
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Polars for GOE 331 (PFALZ 60) AIRFOIL (goe331-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe331-il | 50,000 | 9 | 22.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 9 | 58.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 5 | 57.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 9 | 79.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 9 | 97.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 5 | 94.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 9 | 119.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 5 | 117.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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