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检索条件"主题词=computational fluid dynamics simulation"

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Rough-Wall Turbulent Heat Transfer Experiments in Hypersonic Free Flight

Rough-Wall Turbulent Heat Transfer Experiments in Hypersonic...

引用

AIAA Aviation Forum and Exposition

作者： Wilder, Michael C. Prabhu, Dinesh K. NASA Aerothermodynam Branch Ames Res Ctr MS 230-2 Moffett Field MS 94035 USA Analyt Mech Associates Inc Entry Syst & Technol Div Ms 229-1 Moffett Field MS 94035 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

Rough-wall turbulent heat transfer measurements were obtained on ballistic-range models in hypersonic flight in the NASA Ames Hypervelocity Free Flight Aerodynamic Facility. Each model had three different surface textures on segments of the conic frustum: smooth wall, sand roughness, and a pattern roughness, thereby providing smooth-wall and sand-roughness reference data for each test. The pattern roughness was representative of a woven thermal protection system material developed by NASA's Heatshield for Extreme Entry Environment Technology project. The tests were conducted at launch speeds of 3.2 km/s in air at 0.15 atm. Roughness Reynolds numbers, k(+), ranged for 12 to 70 for the sand roughness, and as high as 200 for the pattern roughness. Boundary-layer parameters required for calculating k(+) were evaluated using computational fluid dynamics simulations. Heat transfer augmentation factors were determined as the ratio of the rough-wall to smooth-wall heat flux measured on each test. For the sand-rough surfaces, the augmentation correlated with roughness Reynolds number, in agreement with Powars' correlation of the Passive Nosetip Technology Program data. Equivalent sand roughness sizes were determined for each pattern roughness using two sand roughness correlations: Dirling and van Rij, et al. The measured heat-flux augmentation for the two larger pattern roughness heights correlated well with roughness Reynolds numbers based on the equivalent sand roughness determined with either sand roughness correlation, but not for the smallest pattern roughness height tested. It has yet to be determined whether this difference is due to limitations in the experimental approach, or due to limits in the equivalent sand roughness correlations used. Future experiments are planned that will include roughness patterns more like those used in developing the equivalent sand roughness correlations.

关键词： Boundary Layer Heat Transfer Thermal Protection System Heat Flux Distribution Boundary Layer Transition Reynolds Numbers Surface Roughness Hypervelocity Free Flight Aerodynamic Facilities Hypersonic Flight NASA Ames Research Center computational fluid dynamics simulation

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Aerodynamic Design Optimization and Shape Exploration using Generative Adversarial Networks

Aerodynamic Design Optimization and Shape Exploration using ...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Chen, Wei Chiu, Kevin Fuge, Mark D. Univ Maryland Dept Mech Engn College Pk MD 20742 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

Global optimization of aerodynamic shapes requires a large number of expensive CFD simulations because of the high dimensionality of the design space. One means to combat that problem is to reduce the dimension of the design space-for example, by constructing low dimensional parametric functions (such as PARSEC and others)-and then optimizing over those parameters instead. Such approaches require first a parametric function that compactly describes useful variation in airfoil shape-a non-trivial and error-prone task. In contrast, we propose to use a deep generative model of aerodynamic designs (specifically airfoils) that reduces the dimensionality of the optimization problem by learning from shape variations in the UIUC airfoil database. We show that our data-driven model both (1) learns realistic and compact airfoil shape representations and (2) empirically accelerates optimization convergence by over an order of magnitude.

关键词： Aerodynamic Shape Optimization Generative Adversarial Network Airfoil Databases computational fluid dynamics simulation XFoil Newton's Method Lift to Drag Ratio Particle Swarm Optimization Optimization Algorithm Bayesian Optimization

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Generalized Entropy Stable Weighted Essentially Non-Oscillatory Finite Difference Scheme in Multi-Block Domains

Generalized Entropy Stable Weighted Essentially Non-Oscillat...

引用

AIAA Aviation Forum and Exposition

作者： Maeng, J. Brad Fisher, Travis C. Carpenter, Mark H. Sandia Natl Labs Computat Thermal & Fluid Mech MS 0828 Albuquerque NM 87123 USA NASA Langley Res Ctr Computat Aerosci Hampton VA 23681 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

A new cell-centered third-order entropy stable Weighted Essentially Non-Oscillatory (SS-WENO) finite difference scheme in multi-block domains is developed for compressible flows. This new scheme overcomes shortcomings of the conventional SSWENO finite difference scheme in multi-domain problems by incorporating non-dissipative Simultaneous Approximation Term (SAT) penalties into the construction of a dual flux. The stencil of the generalized dual flux allows for full stencil biasing across the interface while maintaining the nonlinear stability estimate. We demonstrate the shock capturing improvement across multi-block domain interfaces using the generalized SSWENO in comparison to the conventional entropy stable high-order finite difference with interface penalty in shock problems. Furthermore, we test the new scheme in multi-dimensional turbulent flow problems to assess the accuracy and stability of the multi-block domain formulation.

关键词： Finite Difference Method Entropy One Dimensional Flow Kinetic Energy computational fluid dynamics simulation Freestream Mach Number Sod Shock Tube Taylor Green Vortex Primitive Variable Finite Volume Scheme

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Output-Based Mesh Optimization for the Embedded Discontinuous Galerkin Method

Output-Based Mesh Optimization for the Embedded Discontinuou...

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AIAA Aviation Forum and Exposition

作者： Fidkowski, Krzysztof J. Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

This paper presents a method for optimizing computational meshes for the prediction of scalar output quantities when using the embedded discontinuous Galerkin (EDG) discretization. EDG offers memory and computational time advantages compared to the standard discontinuous Galerkin (DG) method through its decoupling of elemental degrees of freedom and the introduction of continuous face degrees of freedom that become the only globally-coupled unknowns. However, the additional equations of weak flux continuity on each interior face introduce new residuals that augment output error estimates and complicate existing element-centric mesh optimization methods. This work presents a technique for converting face-based error estimates to elements and sampling their reduction with refinement in order to determine element-specific anisotropic convergence rate tensors. The sampling uses fine-space adjoint projections and does not require any additional solves on subelements. Together with a degree-of-freedom cost model, this EDG error model drives metric-based unstructured mesh optimization. Adaptive results for inviscid and viscous two-dimensional flow problems demonstrate (1) improvement of EDG mesh optimality when using the new error model compared to one that does not incorporate face errors, and (2) degree of freedom and computational-time benefits of EDG relative to DG.

关键词： Roe Approximate Riemann Solver Two Dimensional Flow Drag Coefficient Optimization Algorithm Condensation NACA 0012 computational fluid dynamics simulation Three Degrees of Freedom Navier Stokes Equations Stagnation Streamlines

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Lift Fan Assessment for Conceptual Design of Aircraft Forebody

Lift Fan Assessment for Conceptual Design of Aircraft Forebo...

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AIAA Aviation Forum and Exposition

作者： Myers, Leighton M. Czerwiec, Ryan Napolillo, Zachary Naval Air Warfare Ctr Appl Aerodynam & Store Separat Branch Aircraft Div Patuxent River MD 20670 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

This study was conducted to assess the impact that gross changes in forebody geometry have on lift fan inlet suction. Variations in aircraft nose length and width, canopy height, forward fuselage width, and lift fan inlet door scoop were all considered. This resulted in 54 unique geometric configurations. A series of wind tunnel measurements and companion computational fluid dynamics simulations were performed. Trends were observed by examining the pressure distribution inside the lift fan duct and on the surface of the forebody model. The lift fan inlet door and tall canopy were observed to have the most significant impact on duct inlet pressures.

关键词： Air Vehicle Smoke Flow Visualization Low Speed Wind Tunnel Fuselage Configurations computational fluid dynamics simulation Engine Inlet Angle of Attack Free Stream Velocity Separated Flows Sideslip Angle

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Unsteady Flow Characteristics of a Double-side Sliding Pulsed Discharge Plasma Actuation

Unsteady Flow Characteristics of a Double-side Sliding Pulse...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Zheng, Borui Ge, Chang Ke, Xi-zheng Xue, Ming Wang, Yu-Shuai Xian Univ Technol Sch Automat & Informat Engn Xian 710048 Shaanxi Peoples R China Xian Univ Technol Sch Mech & Precis Instrument Engn Xian 710048 Shaanxi Peoples R China Northwestern Polytech Univ Dept Aeronaut & Astronaut Xian 710072 Peoples R China Air Force Engn Univ Sci & Technol Plasma Dynam Lab Xian Peoples R China

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

Plasma actuation is a burgeoning type of active flow control technology. The typical dielectric barrier discharge (DBD) plasma actuators have been investigated intensively by researchers all over the world, but there are still some problems worthy of further studies, for example, the stimulation strength is not strong enough, the region of influence is small, and the control mechanism is not yet clear. This paper proposes a double-side sliding pulsed discharge (abbreviated as DSPD below) plasma actuator which combines pulsed plasma actuation with high DC voltage components. Aiming at the key scientific issue of DSPD plasma actuator, the characteristics of DSPD plasma actuator under the static atmosphere will be revealed through high-speed schlieren system. The flow control ability of DSPD plasma actuator will be verified, and the regularity and rules in the influence of various plasma actuation parameters on flow control effect will be acquired.

关键词： Flow Characteristics Plasma Actuator Dielectric Barrier Discharge Aerodynamic Characteristics Vortex Structure Aerodynamic Flows Electric Field Strength computational fluid dynamics simulation Electrical Energy Permittivity

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The Side-by-Side Urban Air Taxi Concept

The Side-by-Side Urban Air Taxi Concept

引用

AIAA Aviation Forum and Exposition

作者： Diaz, Patricia Ventura Johnsony, Wayne Ahmadz, Jasim Yoonz, Seokkwan NASA Ames Res Ctr Moffett Field CA 94035 USA NASA Ames Res Ctr Adv Supercomputing Div Moffett Field CA 94035 USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

High-fidelity computational fluid dynamics simulations have been carried out in order to analyze the aerodynamics and performance of the side-by-side urban air taxi for urban air mobility. High-order accurate schemes, dual-time stepping, and the delayed detached-eddy simulation model have been employed. The flow solver has been loosely coupled with a rotorcraft comprehensive analysis code. The vehicle simulated is a six-passenger side-by-side intermeshing rotor helicopter with hybrid propulsion for air taxi operations. This multi-rotor concept vehicle is intended to focus and guide NASA research activities in support of aircraft development for emerging aviation markets, in particular vertical take-off and landing air taxi operations.

关键词： Lifting Line Theory computational fluid dynamics simulation Intermeshing Rotors Urban Air Mobility Rotor Systems Vertical Take off and Landing Hybrid Propulsion Air Transportation System Blade Vortex Interaction Vortex Shedding

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Removing Pollution in the Fourier Space Representation of Non-Periodic Signals over Finite Domains

Removing Pollution in the Fourier Space Representation of No...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Paes, Paulo L. K. Xuan, Yuan Shah, Yash G. Brasseur, James G. Penn State Univ Dept Mech Engn University Pk PA 16801 USA Univ Colorado Smead Dept Aerosp Engn Sci Boulder CO 80304 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

We present a strategy to remove the broadband Fourier spectral content associated with the boundary discontinuities in non-periodic directions of signals over finite domains, with negligible modification of the scales of interest in the original signal. The discontinuities arise from the signal decomposition using the Fourier harmonic basis functions that are defined over infinite domain, so the periodically extended signal in non-periodic directions includes a discontinuity at the boundaries between the signal and its periodic extension. The specific Fourier content associated with the non-periodicity of an arbitrary physical signal is identified and a procedure is developed to systemically isolate its spectral content with minimal modification of the original signal. The proposed "discontinuity pollution removal" procedure is first developed for C-0 boundary discontinuities in one-dimensional signals, and then extended to higher order C-N>0 boundary discontinuities in multi-dimensional signals with one non-periodic direction. This procedure allows for the analysis of signals over finite domains with the Fourier decomposition regardless of boundary conditions. We validate and demonstrate the capabilities of the proposed procedure for a test case of engineering relevance.

关键词： Vortex Velocity computational fluid dynamics simulation Turbulent Reacting Flow Nonlinear dynamics Empirical Mode Decomposition Continuous Wavelets Finite Rate Chemical Kinetics Energy Transfer Scale Space Dirichlet Boundary Condition

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Aerodynamic Noise Generated by the NREL Phase VI Wind Turbine Rotor

Aerodynamic Noise Generated by the NREL Phase VI Wind Turbin...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Giridhar, R. Farokhi, S. Taghavi, R. Univ Kansas Aerosp Engn Dept Aerosp Engn Lawrence KS 66045 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

The preliminary step in a computational study to mitigate aerodynamic noise generated by a wind turbine rotor involves accurate prediction of noise generated by wind turbine blades that can be used as a basis for comparison. In this present study, a computational fluid dynamics and computational Aeroacoustics prediction has been made for different inlet wind speeds on the NREL Phase VI wind turbine rotor. Steady CFD analysis was conducted using SST k-omega RANS turbulence model and the flowfield information obtained was used by Curle Broadband Noise Source model to predict the acoustic power distribution on the blade surface. Based on this model, it was found that major noise sources are located near the blade tip and blade trailing edge. Next, unsteady CFD analysis was performed using Improved Delayed Detached Eddy simulation and Ffowcs Williams and Hawkings model was used to predict the Sound Pressure Level at a receiver's location downstream of the rotor. Surface noise generation mechanisms namely thickness and loading noise have been predicted for this wind turbine rotor that operates at low subsonic tip Mach numbers. Loading noise was found to be the dominant noise source. Novel noise mitigation techniques to be used on this rotor have been outlined for the next stage of this analysis.

关键词： Wind Turbine Airfoil National Renewable Energy Laboratory Aerodynamic Characteristics computational fluid dynamics simulation Overall Sound Pressure Level Reynolds Averaged Navier Stokes Spalart Allmaras Turbulence Model Turbulent Boundary Layer Incompressible Flow Wind Tunnel Tests

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Effect of External Rib Structure on Aerodynamic Performance of Thin Wing in Low Reynolds Number

Effect of External Rib Structure on Aerodynamic Performance ...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Tamura, Shun Oyamat, Akira Univ Tokyo Dept Aeronaut & Astronaut Sagamihara Kanagawa 2525210 Japan Inst Space & Astronaut Sci JAXA Sagamihara Kanagawa 2525210 Japan

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

We suggest attaching external ribs on the upper surface of a thin wing to increase its rigidity, where the thin wing was designed for Mars exploration airplane that flies in low Reynolds number flight condition. The idea is that by placing the external rib in the separation bubble on the upper surface, we can improve the rigidity of the wing while minimizing aerodynamic performance degradation. The aerodynamic performance of the wing with external ribs and the wing without external ribs are evaluated by using implicit Large-Eddy simulation (iLES) where Reynolds number, Mach number, and angle of attack are set to 23,000, 0.2, and 3 degrees, respectively. Surprisingly, computational results show that the wing with external ribs outperforms the wing without external ribs in terms of lift and drag. As a result, lift-to-drag ratio is improved by 3.6%. This improvement is mainly caused by the increase in the area of negative pressure region due to the longitudinal vortices produced near the upper surface.

关键词： Aerodynamic Performance Aerodynamic Coefficients Thin Wings Aeroplane computational fluid dynamics simulation Vortex Structure Mars Exploration Pressure Coefficient Lift to Drag Ratio Laminar Separation Bubble

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