GOE 615 AIRFOIL (goe615-il)
GOE 615 AIRFOIL - Gottingen 615 airfoil
| Details | Dat file | Parser | |
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(goe615-il) GOE 615 AIRFOIL Gottingen 615 airfoil Max thickness 13.7% at 29.7% chord. Max camber 5.6% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 615 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0117100 0.0298100
0.0237800 0.0461300
0.0483100 0.0637800
0.0729300 0.0779300
0.0976400 0.0890900
0.1472300 0.1044000
0.1969900 0.1137200
0.2967700 0.1218600
0.3967800 0.1215100
0.4970400 0.1116700
0.5974200 0.0973300
0.6979300 0.0780000
0.7985500 0.0546600
0.8992400 0.0288300
0.9496000 0.0151600
1.0000000 0.0000000
0.0000000 0.0000000
0.0128900 -.0146600
0.0255000 -.0188200
0.0505600 -.0211600
0.0756000 -.0225000
0.1006100 -.0228300
0.1506000 -.0225100
0.2005400 -.0201900
0.3003900 -.0145400
0.4002500 -.0093900
0.5001400 -.0052500
0.6000600 -.0021000
0.7000000 0.0000500
0.7999900 0.0002000
0.8999900 0.0003500
0.9500000 0.0001700
1.0000000 0.0000000
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Similar airfoils
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Polars for GOE 615 AIRFOIL (goe615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe615-il | 50,000 | 9 | 10.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 9 | 51 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 5 | 53 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 9 | 74.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 5 | 72.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 9 | 104.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 5 | 93.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 9 | 125.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 5 | 102.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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