GOE 234 (MVA CA5) AIRFOIL (goe234-il)
GOE 234 (MVA CA5) AIRFOIL - Gottingen 234 (MVA CA5) airfoil
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(goe234-il) GOE 234 (MVA CA5) AIRFOIL Gottingen 234 (MVA CA5) airfoil Max thickness 14.2% at 19.7% chord. Max camber 9.2% at 49.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 234 (MVA CA5) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0117500 0.0292000
0.0239500 0.0407200
0.0484400 0.0606400
0.0730500 0.0759800
0.0977300 0.0884100
0.1472200 0.1080800
0.1969100 0.1200600
0.2965700 0.1333200
0.3964900 0.1365900
0.4966500 0.1303600
0.5970100 0.1164400
0.6975300 0.0962300
0.7982200 0.0692100
0.8990100 0.0386000
0.9494700 0.0207000
1.0000000 0.0037000
0.0000000 0.0000000
0.0128500 -.0135700
0.0254600 -.0180500
0.0505600 -.0217000
0.0756100 -.0237600
0.1006700 -.0260100
0.1506600 -.0255300
0.2005700 -.0221500
0.3000200 -.0008900
0.3992000 0.0311600
0.4986300 0.0532100
0.5984200 0.0613800
0.6985600 0.0560500
0.7988500 0.0446300
0.8994300 0.0220200
0.9497700 0.0089100
1.0000000 -.0037000
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Polars for GOE 234 (MVA CA5) AIRFOIL (goe234-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe234-il | 50,000 | 9 | 10.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 50,000 | 5 | 27.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 9 | 54.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 5 | 56.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 9 | 77 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 5 | 79.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 9 | 110.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 5 | 108.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 9 | 137.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 5 | 127.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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