Topic
Vortex lattice method
About: Vortex lattice method is a research topic. Over the lifetime, 779 publications have been published within this topic receiving 9242 citations.
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TL;DR: In this article, a structural and aero-elastic model for wing sizing and weight calculation of a strut-braced wing is described, which reveals the significant influence of the strut on the bending material weight of the wing.
Abstract: A structural and aeroelastic model for wing sizing and weight calculation of a strut-braced wing is described. The wing weight is calculated using a newly developed analysis accounting for the special nature of strut-braced wings. A specially developed aeroelastic model enables one to consider wing flexibility and spanwise redistribution of the aerodynamic loads during in-flight maneuvers. The structural model uses a hexagonal wing-box featuring skin panels, stringers, and spar caps, whereas the aerodynamics part employs a linearized transonic vortex lattice method. Thus, the wing weight may be calculated from the rigid or flexible wing spanload. The calculations reveal the significant influence of the strut on the bending material weight of the wing. The strut enables one to design a wing featuring thin airfoils without weight penalty. It also influences the spanwise redistribution of the aerodynamic loads and the resulting deformations. Increased weight savings are possible by iterative resizing of the wing structure using the actual design loads. As an advantage over the cantilever wing, the twist moment caused by the strut force results in increased load alleviation, leading to further structural weight savings.
46 citations
28 Jun 2010
TL;DR: This research investigates methods for designing and optimizing winglet geometry for UAVs that operate at Reynolds numbers near 10 and applies the resulting methodology to existing UAV platforms for specific performance improvements.
Abstract: Winglets are known improve the efficiency of large aircraft at high subsonic speeds, but winglet designs for smaller aircraft such as UAVs are largely unproven. Winglets improve efficiency by diffusing the shed wingtip vortex, which in turn reduces the drag due to lift and improves the wing’s lift over drag ratio. This research investigates methods for designing and optimizing winglet geometry for UAVs that operate at Reynolds numbers near 10. The design methodology is based on the vortex lattice method. Optimized designs are tested and compared with base designs for validation and include both Whitcomb and blended winglets. Designs are validated using wind tunnel tests. The resulting methodology is then applied to existing UAV platforms for specific performance improvements.
46 citations
TL;DR: In this paper, a gradient-based optimization algorithm is used to pinpoint the optimal kinematics maximizing the propellent efficiency of a 3D unsteady vortex lattice method.
45 citations
TL;DR: In this article, a nonlinear vortex lattice method (NVLM) was coupled with a vortex particle method (VPM) and used for simulation of the NREL 5MW wind turbine undergoing periodic motions.
44 citations
TL;DR: In this paper, the authors compare rotor blade loading, wake geometry, blade motion and noise radiation in the DNW with rotor simulation codes of different organizations, and validate the results against experimental data obtained from different organizations.
Abstract: Helicopter rotor simulation codes of different organizations are validated against experimental data obtained in the DNW. The comparison addresses rotor blade loading, wake geometry, blade motion and noise radiation. Although specific differences exist the general prediciton of rotor noise is reasonably well.
44 citations