GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
GOE 116 (MVA MK.3) AIRFOIL - Gottingen 116 (MVA MK.3) airfoil
| Details | Dat file | Parser | |
|
(goe116-il) GOE 116 (MVA MK.3) AIRFOIL Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord. Max camber 4.1% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 116 (MVA MK.3) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121900 0.0117200
0.0245000 0.0188500
0.0491900 0.0307000
0.0739500 0.0398500
0.0987200 0.0484000
0.1484000 0.0608100
0.1981600 0.0700200
0.2978100 0.0832500
0.3977000 0.0873800
0.4978000 0.0835200
0.5981000 0.0721600
0.6985199 0.0563100
0.7989800 0.0386500
0.8994500 0.0209000
0.9497000 0.0114200
1.0000000 0.0017500
0.0000000 0.0000000
0.0127100 -.0080700
0.0253500 -.0134300
0.0505300 -.0202700
0.0756300 -.0240100
0.1006700 -.0254500
0.1505600 -.0213300
0.2004300 -.0163200
0.3002600 -.0096900
0.4001600 -.0057600
0.5000600 -.0023200
0.6000100 -.0002900
0.6999800 0.0008400
0.7999700 0.0009800
0.9000000 -.0001800
0.9500300 -.0010700
1.0000000 -.0017500
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GOE 116 (MVA MK.3) AIRFOIL (goe116-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe116-il | 50,000 | 9 | 29.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 9 | 58 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 100,000 | 5 | 56.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 9 | 78.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 200,000 | 5 | 76.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 9 | 106.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 500,000 | 5 | 81.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 9 | 100.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe116-il | 1,000,000 | 5 | 91.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||