GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
GOE 79 (PFALZ 11) AIRFOIL - Gottingen 79 (Pfalz 11) airfoil
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(goe79-il) GOE 79 (PFALZ 11) AIRFOIL Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord. Max camber 6% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 79 (PFALZ 11) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122800 0.0264000
0.0246900 0.0366100
0.0495800 0.0502200
0.0745000 0.0594300
0.0994300 0.0680400
0.1493300 0.0796500
0.1992800 0.0856700
0.2992500 0.0893100
0.3992700 0.0873500
0.4993300 0.0791900
0.5994400 0.0672400
0.6995500 0.0534800
0.7996800 0.0375200
0.8998200 0.0209600
0.9498900 0.0129800
1.0000000 0.0028000
0.0000000 0.0000000
0.0125900 -.0110900
0.0250700 -.0081900
0.0500000 -.0001800
0.0749600 0.0051300
0.0999100 0.0109400
0.1498500 0.0180600
0.1998000 0.0240800
0.2997400 0.0305200
0.3997400 0.0313600
0.4997500 0.0300000
0.5997900 0.0252400
0.6998300 0.0198800
0.7999000 0.0123200
0.8999600 0.0047600
0.9499900 0.0006800
1.0000000 -.0028000
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Polars for GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe79-il | 50,000 | 9 | 59.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 50,000 | 5 | 42.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 9 | 57.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 5 | 59.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 9 | 75.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 9 | 102.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 5 | 97.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 9 | 120.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 5 | 103.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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