GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
GOE 319 (HANSA-BRANDENBURG II) AIRFOIL - Gottingen 319 (Hansa-Brandenburg II) airfoil
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(goe319-il) GOE 319 (HANSA-BRANDENBURG II) AIRFOIL Gottingen 319 (Hansa-Brandenburg II) airfoil Max thickness 10.3% at 29.8% chord. Max camber 5.8% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 319 (HANSA-BRANDENBURG II) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120600 0.0306700
0.0243700 0.0438500
0.0491100 0.0617100
0.0739200 0.0745700
0.0987900 0.0839300
0.1486000 0.0967500
0.1985100 0.1033700
0.2984300 0.1088100
0.3984600 0.1065600
0.4986000 0.0968000
0.5988100 0.0823500
0.6990800 0.0637000
0.7993600 0.0439500
0.8996800 0.0220000
0.9498400 0.0113300
1.0000000 0.0005500
0.0000000 0.0000000
0.0127000 -.0139200
0.0252100 -.0146400
0.0501800 -.0127700
0.0751400 -.0099100
0.1001000 -.0069500
0.1500300 -.0023300
0.1999700 0.0022900
0.2999100 0.0063300
0.3999100 0.0062800
0.4999300 0.0047200
0.5999400 0.0041700
0.6999600 0.0026100
0.7999800 0.0014600
0.9000100 -.0008900
0.9500200 -.0012700
1.0000000 -.0005500
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Polars for GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe319-il | 50,000 | 9 | 26.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 50,000 | 5 | 36.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 100,000 | 9 | 53.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 100,000 | 5 | 55.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 200,000 | 9 | 75.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 200,000 | 5 | 71.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 500,000 | 9 | 101.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 500,000 | 5 | 91.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe319-il | 1,000,000 | 9 | 114 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe319-il | 1,000,000 | 5 | 112.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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