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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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Reference EntryDOI
25 Jan 2018
01 Jan 1997
TL;DR: In this paper, the generalized vortex lattice method for oscillating lifting surfaces in subsonic flow is extended to the supersonic planar regime, where the lifting surfaces are assumed to be convex.
Abstract: The generalized vortex lattice method for oscillating lifting surfaces in subsonic flow is extended to the supersonic planar regime.
Proceedings ArticleDOI
15 Sep 2015
TL;DR: In this paper, the effects of synthetic jet actuators (SJAs) on aircraft wings using a reduced order model (ROM) were analyzed for determining the unsteady aerodynamic forces modified by the presence of the SJAs.
Abstract: The implementation of Synthetic Jet Actuators (SJAs) on Unmanned Aerial Vehicles (UAVs) provides a safe test-bed for analysis of improved performance, in the hope of certification of this technology on commercial aircraft in the future. The use of high resolution numerical methods (i.e. CFD) to capture the details of the effects of SJAs on flows and on the hosting lifting surface are computationally expensive and time-consuming, which renders them ineffective for use in real-time flow control implementations. Suitable alternatives include the use of Reduced Order Models (ROMs) to capture the lower resolution overall effects of the jets on the flow and the hosting structure. This research paper analyses the effects of SJAs on aircraft wings using a ROM for the purpose of determining the unsteady aerodynamic forces modified by the presence of the SJAs. The model developed is a 3D unsteady panel code where the jets are represented by source panels. This code has the ability to model thick 3D trapezoidal wings with sweep and dihedral, accepting any aerofoil coordinate file. Multiple rows of SJAs can also be applied where desired. In order to validate the panel code, comparisons are made with past experimental data and other numerical methods like the vortex lattice method and CFD. There is avenue for further work in implementing a robust control architecture around SJA technologies, which in the future could serve as replacements for traditional hinged flight control surfaces and flutter suppression solutions.
08 Dec 2010
TL;DR: In this article, aerodynamic tests were conducted at UPT-Laboratorium Aero Gasdinamika dan Getaran (LAGG)-BPPT, PUSPIPTEK, Serpong, to determine the performance of the lift and pre-take off craft conditions.
Abstract: This paper describes aerodynamic tests (wind tunnel tests) for a model of Wing in Surface Effect Craft 8 seater, WiSE-8. The tests were conducted at UPT-Laboratorium Aero Gasdinamika dan Getaran (LAGG)-BPPT, PUSPIPTEK, Serpong, to determine the performance of the lift and pre-take off craft conditions. This craft model with scale of 1 per 6 was tested with rigid body - upside up - power off method. The profile of craft wing model was aerofoil form, Clark-Y. The craft model test with complete configuration (Wing-Body-Pontoon-Nacelle-Tail) was carried out with the following parameters, wind speed of 20, 30, 40, and 50 m per sec, angle of attack of -6 to 18 degree, yaw angle of 0 degree, ground board height 0-1 m (in respect to prototype value of 0-6 m). Meanwhile,the tests of air flow visualization were carried out by using wool tuft at speed of 40 m per sec. The result of wind tunnel test consisting of CL, CD, CM, and CL-CD was validated by theoritical calculation using Vortex Lattice Method (VLM) and Datcom software. Then this result was evaluated and extrapolated to predict the movement of WiSE-8 in the pre take off performance condition, especially in the longitudinal direction.

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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20221
202133
202036
201947
201837
201731