GOE 121 (MVA H.1) AIRFOIL (goe121-il)
GOE 121 (MVA H.1) AIRFOIL - Gottingen 121 (MVA H.1) airfoil
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(goe121-il) GOE 121 (MVA H.1) AIRFOIL Gottingen 121 (MVA H.1) airfoil Max thickness 6.7% at 19.9% chord. Max camber 4.6% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 121 (MVA H.1) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122800 0.0153700
0.0246700 0.0230500
0.0494900 0.0359000
0.0743700 0.0443600
0.0992500 0.0529100
0.1491100 0.0628200
0.1990100 0.0700300
0.2989300 0.0752400
0.3989400 0.0744600
0.4990100 0.0693900
0.5991200 0.0621100
0.6993000 0.0498300
0.7994900 0.0362500
0.8997200 0.0197800
0.9498300 0.0118900
1.0000000 0.0010000
0.0000000 0.0000000
0.0126700 -.0123200
0.0251900 -.0142400
0.0502100 -.0144900
0.0751800 -.0125300
0.1001200 -.0083800
0.1500300 -.0022700
0.1999500 0.0036400
0.2998000 0.0139600
0.3997500 0.0175800
0.4997500 0.0179000
0.5997900 0.0150200
0.6998300 0.0120400
0.7998700 0.0091600
0.8999299 0.0051800
0.9499500 0.0022800
1.0000000 -.0010000
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Polars for GOE 121 (MVA H.1) AIRFOIL (goe121-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe121-il | 50,000 | 9 | 40.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 50,000 | 5 | 43.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 100,000 | 9 | 60.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 100,000 | 5 | 59.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 200,000 | 9 | 79.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 200,000 | 5 | 74.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 500,000 | 9 | 99.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 500,000 | 5 | 87 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe121-il | 1,000,000 | 9 | 104.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe121-il | 1,000,000 | 5 | 97.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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