Swept wing vorticity analysis
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About
This repository contains results of the swept wing vorticity study using OpenVSP software.
Parameters
The study was performed for a wing with the taper ratio 0.75 and for a NACA 1412 airfoil
The analysis was performed for several wing parameters:
- Aspect ratio (AR): 6, 7, 8, 9
- Wing sweep angle (gamma): 12, 15, 18 degrees
- Angle of attack (AoA): 0, 5, 10 degrees
Results
Results of lift coefficient distribution along the half wing span were normalized by the 'ideal' Cl values - for a rectangular wing with AR=20
CCl - normalized lift coefficient
CCl *c/cref - normalized lift coefficient reduced by local chord
References
[1] M. Niță, Dieter Scholz, Estimating The Oswald Factor From Basic Aircraft Geometrical Parameters (https://www.fzt.haw-hamburg.de/pers/Scholz/OPerA/OPerA_PUB_DLRK_12-09-10.pdf)
About
This repository contains results of the swept wing vorticity study using OpenVSP software.
Parameters
The study was performed for a wing with the taper ratio 0.75 and for a NACA 1412 airfoil
The analysis was performed for several wing parameters:
- Aspect ratio (AR): 6, 7, 8, 9
- Wing sweep angle (gamma): 12, 15, 18 degrees
- Angle of attack (AoA): 0, 5, 10 degrees
Results
Results of lift coefficient distribution along the half wing span were normalized by the 'ideal' Cl values - for a rectangular wing with AR=20
CCl - normalized lift coefficient
CCl *c/cref - normalized lift coefficient reduced by local chord
References
[1] M. Niță, Dieter Scholz, Estimating The Oswald Factor From Basic Aircraft Geometrical Parameters (https://www.fzt.haw-hamburg.de/pers/Scholz/OPerA/OPerA_PUB_DLRK_12-09-10.pdf)
