Airfoil
Mostrando 1-12 de 52 artigos, teses e dissertações.
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1. Numerical Simulation of a Pitching Airfoil Under Dynamic Stall of Low Reynolds Number Flow
ABSTRACT: In this research, viscous, unsteady and turbulent fluid flow is simulated numerically around a pitching NACA0012 airfoil in the dynamic stall area. The Navier-Stokes equations are discretized based on the finite volume method and are solved by the PIMPLE algorithm in the open source software, namely OpenFOAM. The SST k - ω model is used as the tur
J. Aerosp. Technol. Manag.. Publicado em: 14/11/2019
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2. Investigation of a NACA0012 Finite Wing Aerodynamics at Low Reynold’s Numbers and 0º to 90º Angle of Attack
ABSTRACT: The aerodynamic characteristics of a NACA0012 wing geometry at low Reynold’s numbers and angle of attack ranging from 0º to 90º are investigated using numerical simulations and the results are validated by wind tunnel experiments. Further experiments are conducted at low Reynold’s numbers of 1 × 105, 2 × 105 and 3 × 105. Findings of the st
J. Aerosp. Technol. Manag.. Publicado em: 28/03/2019
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3. Experimental and Numerical Study of the Unsteady Wake of a Supercritical Airfoil in a Compressible Flow
ABSTRACT Experimental investigations were carried out to study the wake profile of a supercritical airfoil at Mach numbers of 0.4 and 0.6 in a pitching motion. Both static and dynamic tests were conducted in a tri-sonic wind tunnel. Flow field inside the wake was measured by hot wire anemometry at downstream distances of 0.25 and 0.5 times the chord length f
J. Aerosp. Technol. Manag.. Publicado em: 10/12/2018
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4. Improvement of Airfoils Aerodynamic Efficiency by Thermal Camber Phenomenon at Low Reynolds Number
ABSTRACT: In this research, viscous, laminar and steady flow around symmetric and non-symmetric airfoils is simulated at Low Reynolds Number (LRN). Navier-Stokes (N-S) equations are discretized by Finite Volume Method (FVM) and are solved by the SIMPLE algorithm in an open source software, namely OpenFOAM. The main objective of this paper is the introduction
J. Aerosp. Technol. Manag.. Publicado em: 01/11/2018
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5. Computational Investigation on the Effects of Two-Way Wing Morphing Strategy in the Critical Mach Number
ABSTRACT: The elasto-flexible wing morphing is an advanced methodology to achieve higher lift-to-drag (L/D) ratio for the subsonic wing configurations at the given flow conditions. The present article describes mechanisms of continuous morphing of a swept back wing for achieving effective delay in the critical Mach number (Mcr) distribution over the wing sur
J. Aerosp. Technol. Manag.. Publicado em: 08/03/2018
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6. Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge
ABSTRACT: Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-to-drag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous dur
J. Aerosp. Technol. Manag.. Publicado em: 02/10/2017
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7. Detailed Numerical Study on the Aerodynamic Behavior of a Gurney Flapped Airfoil in the Ultra-low Reynolds Regime
ABSTRACT: The addition of Gurney flap changes the nature of flow around airfoil by producing asymmetric Von-Karman vortex in its wake. Most of the investigations on Gurney flapped airfoils have modeled the flow using a quasi-steady approach, resulting in time-averaged values with no information on the unsteady features of the flow. Among these, some investig
J. Aerosp. Technol. Manag.. Publicado em: 2017-06
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8. Design Analysis of Solar-Powered Unmanned Aerial Vehicle
ABSTRACT One of the main problems in micro unmanned aerial vehicles is endurance or flight time since the general domain aircraft uses conventional fuel, which is a pollutant, has a limited life and is costly. Then, there is a huge demand for using an unlimited non-exhaustible source of energy. Solar energy is one of the unlimited available renewable energy
J. Aerosp. Technol. Manag.. Publicado em: 2016-12
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9. Wind Tunnel Testing on a Generic Model of a Hybrid Lifting Hull
ABSTRACT In this research, an experimental investigation was carried out at the International Islamic University Malaysia - Low Speed Wind Tunnel facility on a generic model of a hybrid lifting hull. Based on the historical trends of non-rigid airships, the fineness ratio of the said hull has been selected equal to 4. Free stream velocity was kept at 20 m/s
J. Aerosp. Technol. Manag.. Publicado em: 2016-12
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10. Numerical Study of Reduced Frequency Effect on Longitudinal Stability Derivatives of Airfoil under Pitching and Plunging Oscillations
ABSTRACT In this study, incompressible, unsteady and turbulent flow over an airfoil with pitching and plunging oscillations is numerically studied in order to investigate the effect of reduced frequency on stability derivatives of oscillating airfoil. Linear k – ε model called Launder-Sharma and Rhie and Chow model are used for turbulence modeling and ove
J. Aerosp. Technol. Manag.. Publicado em: 2016-09
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11. An Implementation of Self-Organizing Maps for Airfoil Design Exploration via Multi-Objective Optimization Technique
ABSTRACT Design candidates obtained from optimization techniques may have meaningful information, which provides not only the best solution, but also a relationship between object functions and design variables. In particular, trade-off studies for optimum airfoil shape design involving various objectives and design variables require the effective analysis t
J. Aerosp. Technol. Manag.. Publicado em: 2016-06
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12. Numerical Simulation of the Wake Structure and Thrust/Lift Generation of a Pitching Airfoil at Low Reynolds Number Via an Immersed Boundary Method
ABSTRACT: In this study, an accurate computational algorithm in the context of immersed boundary methods is developed and used to analyze an incompressible flow around a pitching symmetric airfoil at Reynolds number (Re = 255). The boundary conditions are accurately implemented by an iterative procedure applied at each time step, and the pressure is also upd
J. Aerosp. Technol. Manag.. Publicado em: 2015-09