Combining Simulation and Experiment for Acoustic-Load Identification.
Abstract not provided.
Lopp, Garret↗
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Characterization of the acoustic field generated by a horn shaped ultrasonic transducer
A horn shaped Langevin ultrasonic transducer used in a single axis levitator was characterized to better understand the role of the acoustic profile in establishing stable traps. The method of characterization included acoustic beam profiling performed by raster scanning an ultrasonic microphone as well as finite element analysis of the horn and its interface with the surrounding air volume. The results of the model are in good agreement with measurements and demonstrate the validity of the approach for both near and far field analyses. Our results show that this style of transducer produces a strong acoustic beam with a total divergence angle of 10 degree, a near-field point close to the transducer surface and a virtual sound source. These are desirable characteristics for a sound source used for acoustic trapping experiments
acoustic, horn, levitation, acoustic simulation↗
Stimulus coding in the cochlear nucleus.
Stimulus coding in cochlear nucleus, noting different discharge patterns of units in different subdivisions
PHYSIOLOGICAL RESPONSE↗
Backscatter of electromagnetic waves from a rough layer.
Backscatter of electromagnetic waves from rough layer simulated by acoustic backscattering from partially submerged Plexiglas layer
ELECTROMAGNETIC SCATTERING↗
Aerospace noise.
Engine generated and in-flight noise environment problems of space vehicles analyzed, using theoretical methods and scale model wind tunnel tests
SCALE MODEL↗
Study of critical defects in ablative heat shield systems for the space shuttle
Experimental results are presented for a program conducted to determine the effects of fabrication-induced defects on the performance of an ablative heat shield material. Exposures representing a variety of space shuttle orbiter mission environments-humidity acoustics, hot vacuum and cold vacuum-culuminating in entry heating and transonic acoustics, were simulated on large panels containing intentional defects. Nondestructive methods for detecting the defects, were investigated. The baseline materials were two honeycomb-reinforced low density, silicone ablators, MG-36 and SS-41. Principal manufacturing-induced defects displaying a critical potential included: off-curing of the ablator, extreme low density, undercut (or crushed) honeycomb reinforcements, and poor wet-coating of honeycomb.
Miller, C. C.↗
On some structure-turbulence interaction problems
The interactions between a turbulent flow structure; responding to its excitation were studied. The turbulence was typical of those associated with a boundary layer, having a cross-spectral density indicative of convection and statistical decay. A number of structural models were considered. Among the one-dimensional models were an unsupported infinite beam and a periodically supported infinite beam. The fuselage construction of an aircraft was then considered. For the two-dimensional case a simple membrane was used to illustrate the type of formulation applicable to most two-dimensional structures. Both the one-dimensional and two-dimensional structures studied were backed by a cavity filled with an initially quiescent fluid to simulate the acoustic environment when the structure forms one side of a cabin of a sea vessel or aircraft.
Maekawa, S.↗
Reduction of rotor-turbulence interaction noise in static fan noise testing
Three effective inlet cleanup methods are described. A flared reverse cone inlet is used to eliminate wakes from the fan casings and/or probe supports. Boundary layer suction is employed ahead of the fan rotor and on the outer flare of the cone to reduce the boundary layer turbulence and remove any residual wakes. To reduce the midstream turbulent intensity and length scales, a turbulence control structure is used which is constructed with both a layer of honeycomb and a fine mesh screen. The effects of these cleanup methods are quantified by measuring the far-field noise in an anechoic chamber, using a high-speed 20-in.-diam fan of the current high passband type. The changes in the turbulent field impinging on this rotor are quantified by mapping the streamwise and transverse turbulent properties (spectra, intensity and length scale) with crossed hot film probes. It is convincingly shown that it is possible to clean up the inlet flow of a static fan noise test facility to a point where the static acoustic data simulate flight data.
Kantola, R. A.↗
Assessment of Total Variation Diminishing schemes in combustion instability problems
Numerical simulations of acoustic waves in a shear layer and in an idealized combustion chamber using high resolution Total Variation Diminishing (TVD) schemes has been carried out to study the effects of inherent scheme dissipation and dispersion errors of this class of problems. The numerical results are compared against available exact solutions to quantify these errors. Several popular TVD limiters widely used in the Computational Fluid Dynamics (CFD) community have been assessed. Osher-Chakravarthy limiters are modified so that they can be used in explicit schemes. Among all the limiters investigated, Osher-Chakravarthy third-order limiter is identified as having performed the best. It is also found that all TVD schemes have exceptionally small dispersive errors.
Wang, Z. J.↗
An Investigation of High-Order Shock-Capturing Methods for Computational Aeroacoustics
Topics covered include: Low-dispersion scheme for nonlinear acoustic waves in nonuniform flow; Computation of acoustic scattering by a low-dispersion scheme; Algorithmic extension of low-dispersion scheme and modeling effects for acoustic wave simulation; The accuracy of shock capturing in two spatial dimensions; Using high-order methods on lower-order geometries; and Computational considerations for the simulation of discontinuous flows.
Casper, Jay↗
An Investigation of the Flow Physics of Acoustic Liners by Direct Numerical Simulation
This report concentrates on reporting the effort and status of work done on three dimensional (3-D) simulation of a multi-hole resonator in an impedance tube. This work is coordinated with a parallel experimental effort to be carried out at the NASA Langley Research Center. The outline of this report is as follows : 1. Preliminary consideration. 2. Computation model. 3. Mesh design and parallel computing. 4. Visualization. 5. Status of computer code development. 1. Preliminary Consideration.
Watson, Willie R.↗
A Parameter Identification Method for Helicopter Noise Source Identification and Physics-Based Semi-Empirical Modeling
A new physics-based parameter identification method for rotor harmonic noise sources is developed using an acoustic inverse simulation technique. This new method allows for the identification of individual rotor harmonic noise sources and allows them to be characterized in terms of their individual non-dimensional governing parameters. This new method is applied to both wind tunnel measurements and ground noise measurements of two-bladed rotors. The method is shown to match the parametric trends of main rotor Blade-Vortex Interaction (BVI) noise, allowing accurate estimates of BVI noise to be made for operating conditions based on a small number of measurements taken at different operating conditions.
Greenwood, Eric, II↗
Simulation of Ares Scale Model Acoustic Test Overpressure Transients Using Computational Fluid Dynamics
No abstract available
Putnam, Gabriel↗
Towards Multiphase Simulations of Launch Environments for Acoustic Predictions
Explore the source record for details and available documents.
EGS↗
Nonlinear acoustic wave propagation in atmosphere
A model problem that simulates an atmospheric acoustic wave propagation situation that is nonlinear is considered. The model is derived from the basic Euler equations for the atmospheric flow and from the regular perturbations for the acoustic part. The nonlinear effects are studied by obtaining two successive linear problems in which the second one involves the solution of the first problem. Well posedness of these problems is discussed and approximations of the radiation boundary conditions that can be used in numerical simulations are presented.
Hariharan, S. I.↗
Near field to far field transformations and multiple beam forming and steering
The feasibility of acoustic verification of microwave near field to far field transformation algorithms using the Phased Array Sonic Simulation System was studied. Existing electromagnetic near field measurement techniques and transformation algorithms (equations) were investigated. It was analytically determined that acoustic verification is valid. Acoustic simulation of electromagnetic near field to far field transformations is emphasized. The acoustic simulation of electromagnetic near field to far field transformation is verified for the modal expansion method. In the modal expansion method, data from antenna near field measurements are converted to a summation or spectrum of modes corresponding to wave numbers in the measurement coordinate system. Fourier transformation of those measurements preserves the far field information in a spectral form that is then readily extractable.
Source record↗
Simulation of Shuttle launch G forces and acoustic loads using the NASA Ames Research Center 20G centrifuge
The high cost and long times required to develop research packages for space flight can often be offset by using ground test techniques. This paper describes a space shuttle launch and reentry simulating using the NASA Ames Research Center's 20G centrifuge facility. The combined G-forces and acoustic environment during shuttle launch and landing were simulated to evaluate the effect on a payload of laboratory rates. The launch G force and acoustic profiles are matched to actual shuttle launch data to produce the required G-forces and acoustic spectrum in the centrifuge test cab where the rats were caged on a free-swinging platform. For reentry, only G force is simulated as the aero-acoustic noise is insignificant compared to that during launch. The shuttle G-force profiles of launch and landing are achieved by programming the centrifuge drive computer to continuously adjust centrifuge rotational speed to obtain the correct launch and landing G forces. The shuttle launch acoustic environment is simulated using a high-power, low-frequency audio system. Accelerometer data from STS-56 and microphone data from STS-1 through STS-5 are used as baselines for the simulations. This paper provides a description of the test setup and the results of the simulation with recommendations for follow-on simulations.
Shaw, T. L.↗
Cavitating Acoustics Modeling in Sierra/SD
Motivated by the need to simulate the effects of underwater explosion on ship structures, we develop a new cavitating acoustics formulation. The proposed approach is consistent with existing methods where the cavitation phenomenon is captured with a bilinear constitutive law. However, the new formulation is in terms of velocity potential, as opposed to the existing displacement-potential and pressure formulations. Also unique to the proposed formulation is a new generalized time-stepping procedure specific to cavitating acoustics, which has the ability to introduce numerical damping to control frothing. Numerical examples of varying complexity are presented to illustrate the effectiveness of the proposed approach and the ability to use velocity potential as a primary field variable for cavitating acoustics simulations.
45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEF↗