GOE 144 (MVA H.21) AIRFOIL (goe144-il)
GOE 144 (MVA H.21) AIRFOIL - Gottingen 144 (MVA H.21) airfoil
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(goe144-il) GOE 144 (MVA H.21) AIRFOIL Gottingen 144 (MVA H.21) airfoil Max thickness 7.3% at 19.9% chord. Max camber 4.7% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 144 (MVA H.21) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122600 0.0157800
0.0246300 0.0249700
0.0494000 0.0397400
0.0742600 0.0491100
0.0991500 0.0564900
0.1489800 0.0680300
0.1988800 0.0748800
0.2987800 0.0813800
0.3988000 0.0799800
0.4989000 0.0732800
0.5990500 0.0635900
0.6992199 0.0519900
0.7994200 0.0387900
0.8996900 0.0208000
0.9498200 0.0117500
1.0000000 0.0000000
0.0000000 0.0000000
0.0126400 -.0092100
0.0251800 -.0118200
0.0502100 -.0142500
0.0751900 -.0128700
0.1001700 -.0113000
0.1500700 -.0043500
0.1999700 0.0019000
0.2998200 0.0118000
0.3997800 0.0144000
0.4997800 0.0148000
0.5998000 0.0139500
0.6998200 0.0122000
0.7998800 0.0080000
0.8999400 0.0041000
0.9499700 0.0020500
1.0000000 0.0000000
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Polars for GOE 144 (MVA H.21) AIRFOIL (goe144-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe144-il | 50,000 | 9 | 38.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe144-il | 50,000 | 5 | 41.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe144-il | 100,000 | 9 | 59 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe144-il | 100,000 | 5 | 60.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe144-il | 200,000 | 9 | 79.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe144-il | 200,000 | 5 | 78 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe144-il | 500,000 | 9 | 106.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe144-il | 500,000 | 5 | 98.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe144-il | 1,000,000 | 9 | 125.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe144-il | 1,000,000 | 5 | 95.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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