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Showing 1 to 20 of 60 for “"Naca 0012"”.
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Dynamic stall of a NACA 0012 airfoil in laminar flow
Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.
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Post-stall hysteresis and flow field unsteadiness on an NACA 0012 airfoil
… associated with static stall hysteresis on an NACA 0012 airfoil at Rec = 1.0 × 10^6. Unsteady pressure measurements were acquired to evaluate the performance of the airfoil, and a hysteresis loop was identified in the vicinity of the airfoil Cl,max. Two fundamentally different flow regimes were …
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Reynolds number effects on the unsteady aerodynamic behavior of an NACA 0012 airfoil
Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 1986
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Convection from ice roughness surfaces using scaled Reynolds numbers for larger NACA 0012 airfoils.
… flow similar to that experienced by a 21-in. NACA 0012 airfoil. The current study characterizes the convective heat transfer using the same roughness surfaces but exposed to flow scaled to that of a larger NACA 0012 airfoil by increasing wind tunnel velocity and thus scaling the Reynolds …
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An experimental low Reynolds number comparison of a Wortmann FX67-K170 airfoil, a NACA 0012 airfoil, and a NACA 64-210 airfoil in simulated heavy rain
Thesis: M.S., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 1987
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Validation and Verification of the Wray-Agarwal Turbulence and Algebraic Transition Models for 2D External Airfoil Flows
… turbulence models. Flow past several symmetric NACA airfoils, namely NACA 0012, NACA 0015 and NACA 0018 are standard test cases for validating and evaluating turbulence models’ accuracy since the experimental data is available for these airfoils. Available wind tunnel data allows for testing …
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Rotor eólico Darrieus: um estudo experimental
… rotor with straight an.d troposkien blades using NACA 0012 and NACA 0015 profiles was realized. A reduzed scale model (height = diameter = 500 mm) with "Prony" brake dynamometer was tested in a wind tunnel with a 1 m2 test section and maximum wind velocity of 8,0 m/s. The experimental results were …
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Aerodynamics and Acoustics of the Virginia Tech Stability Tunnel Anechoic System
… and aeroacoustic characteristics of a NACA 0012 airfoil model over a range of angles of attack and Reynolds numbers. These measurements show that acoustically treating the walls of the circuit both upstream and downstream of the test section, as well as the fan, result in an overall …
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An Approach to Incorporate Additive Manufacturing and Rapid Prototype Testing for Aircraft Conceptual Design to Improve MDO Effectiveness
… cost and time of production. Furthermore, a NACA 0012 model with 20% chord flap was manufactured. Both models were tested in the Virginia Tech (VT) Open-Jet WT for force and moment acquisition. A 1/15th scale ICE 101 model was prepared for manufacturing, but limits of FDM(TM) technology were …
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Mean Flow Characteristics and Turbulent Structures of Turbulent Boundary Layers in Varying Pressure Gradients and Reynolds Numbers
… Wind Tunnel with a 0.914 m chord length, NACA 0012 Airfoil in the test section. This airfoil was rotated to different angles of attack to induce varying pressure gradients on the boundary layer developing on the test section walls. Mean pressure measurements, boundary layer pressure …
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A Higher Order Accurate Finite Element Method for Viscous Compressible Flows
… a wall and subsonic and transonic flows past a NACA 0012 airfoil and laminar flows including flow past a a flat plate and flow past a NACA 0012 airfoil are included to qualitatively evaluate the accuracy of the discretizations. The scheme achieves higher order accuracy without modification. …
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Clean Wing Airframe Noise Modeling for Multidisciplinary Design and Optimization
… cases that were selected from a two-dimensional NACA 0012 experimental database. The agreement between the experiment and the predictions obtained with the new noise metric was very good at various speeds, angles of attack, and Reynolds Number, which showed that the noise metric is capable of …
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Numerical studies of the flow around an airfoil at low Reynolds number
… of laminar separation bubbles formed on a NACA-0012 airfoil at Rec = 5 £ 104 and incidence 5± is investigated. Initially volume forcing is introduced in order to promote transition to turbulence. After obtaining sufficient data from this forced case, the explicitly added disturbances are …
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An Investigation of the Dynamic Effects of Flap Deflection on the Aerodynamic Characteristics of an Airplane Wing Using Computational Fluid Dynamics
… modeled with a moving mesh and was attached to a NACA 0012 airfoil and a wing of a general aviation aircraft for a 2D and 3D investigation, respectively. In addition, the flap deflection rates were varied to investigate their effect on the flow field and the airfoil's stability characteristics. …
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Convection from laser-scanned ice roughness at multiple accretion vent times.
… accelerating flow similar to that experienced by NACA 0012 airfoil and flow with negligible acceleration. The velocity boundary layer development along these surfaces was characterized as well. Each of the roughness surfaces was exposed to similar supercooled cloud conditions for different lengths …
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Airfoil response to periodic disturbances: the unsteady Kutta condition
Unsteady flow fields over a NACA 0012 at an angle of attack are investigated. The first is the classical pitching motion about the airfoil's quarter chord. The second is the flow over a fixed airfoil immersed in the wake of the pitching airfoil. Large reduced frequencies are considered. …
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Transonic aerodynamics of dense gases
… for two-dimensional, steady state, flow over a NACA 0012 airfoil was predicted analytically. The computer code used to model the dense gas behavior was a modified version of Jameson's FLOS2 airfoil code. The modifications to the code enabled modeling the dense gas behavior near the saturated …
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Airfoil Self-Noise Prediction Using Neural Networks for Wind Turbines
… The experimental data corresponds to the NACA 0012, Delft DU96, Sandia S831, S822 and S834, Fx63-137, SG6043 and SD-2030 airfoils. The chord of these airfoils range from 0.025 to 0.91 m and they were tested at Reynolds numbers of up to 3.8 million and angle of attack up to 15° depending on …
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Effect of Flow-Acoustic Resonant Interactions on Aerodynamic Response of Transitional Airfoils
… regime with Rec=10,000 and M=0.2. The symmetric NACA-0012 and the cambered SD7003 airfoils are investigated at various angles of attack that have been found previously to include both the tone and no-tone producing regimes, with specific focus on the aerodynamic lift response. Additional …
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Effect of large distributed roughness near an airfoil leading edge on boundary layer development and transition
… were carried out on a two-dimensional NACA 0012 airfoil with a 21"" chord. The distributed roughness used was in the form of densely packed large hemispherical elements applied to the leading-edge region of the airfoil section. The size of the distributed roughness was greater than or …
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