Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 4
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Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 4
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-23
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 4 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-23 with categories.
The Unified AeroAcoustic Program (UAAP) code calculates the airloads on a single rotation prop-fan, or propeller, and couples these airloads with an acoustic radiation theory, to provide estimates of near-field or far-field noise levels. The steady airloads can also be used to calculate the nonuniform velocity components in the propeller wake. The airloads are calculated using a three dimensional compressible panel method which considers the effects of thin, cambered, multiple blades which may be highly swept. These airloads may be either steady or unsteady. The acoustic model uses the blade thickness distribution and the steady or unsteady aerodynamic loads to calculate the acoustic radiation. The users manual for the UAAP code is divided into five sections: general code description; input description; output description; system description; and error codes. The user must have access to IMSL10 libraries (MATH and SFUN) for numerous calls made for Bessel functions and matrix inversion. For plotted output users must modify the dummy calls to plotting routines included in the code to system-specific calls appropriate to the user's installation. Menthe, R. W. and Mccolgan, C. J. and Ladden, R. M. Unspecified Center AEROACOUSTICS; AERODYNAMIC NOISE; AIRCRAFT NOISE; HIGH SPEED; PROP-FAN TECHNOLOGY; PROPELLER FANS; TURBOPROP AIRCRAFT; USER MANUALS (COMPUTER PROGRAMS); AERODYNAMIC LOADS; BESSEL FUNCTIONS; MATRICES (MATHEMATICS); NOISE INTENSITY; PANEL METHOD (FLUID DYNAMICS); PLOTTING; SOUND WAVES; UNSTEADY AERODYNAMICS; VELOCITY DISTRIBUTION...
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 1 Development Of Theory For Blade Loading Wakes And Noise
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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher: Independently Published
Release Date : 2018-11-17
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 1 Development Of Theory For Blade Loading Wakes And Noise written by National Aeronautics and Space Adm Nasa and has been published by Independently Published this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-11-17 with Science categories.
A unified theory for the aerodynamics and noise of advanced turboprops are presented. Aerodynamic topics include calculation of performance, blade load distribution, and non-uniform wake flow fields. Blade loading can be steady or unsteady due to fixed distortion, counter-rotating wakes, or blade vibration. The aerodynamic theory is based on the pressure potential method and is therefore basically linear. However, nonlinear effects associated with finite axial induction and blade vortex flow are included via approximate methods. Acoustic topics include radiation of noise caused by blade thickness, steady loading (including vortex lift), and unsteady loading. Shielding of the fuselage by its boundary layer and the wing are treated in separate analyses that are compatible but not integrated with the aeroacoustic theory for rotating blades. Hanson, D. B. Unspecified Center AEROACOUSTICS; AIRCRAFT NOISE; COUNTER ROTATION; FLOW DISTRIBUTION; HIGH SPEED; TURBOPROP AIRCRAFT; VIBRATION; VORTICES; APPROXIMATION; BOUNDARY LAYERS; DISTORTION; FUSELAGES; LOADS (FORCES); NONLINEARITY; NONUNIFORMITY; SHIELDING; THICKNESS; WAKES; WINGS...
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 1 Development Of Theory For Blade Loading Wakes And Noise
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Author : D. B. Hanson
language : en
Publisher:
Release Date : 1991
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 1 Development Of Theory For Blade Loading Wakes And Noise written by D. B. Hanson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with categories.
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 3
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-23
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 3 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-23 with categories.
Results of the program for the generation of a computer prediction code for noise of advanced single rotation, turboprops (prop-fans) such as the SR3 model are presented. The code is based on a linearized theory developed at Hamilton Standard in which aerodynamics and acoustics are treated as a unified process. Both steady and unsteady blade loading are treated. Capabilities include prediction of steady airload distributions and associated aerodynamic performance, unsteady blade pressure response to gust interaction or blade vibration, noise fields associated with thickness and steady and unsteady loading, and wake velocity fields associated with steady loading. The code was developed on the Hamilton Standard IBM computer and has now been installed on the Cray XMP at NASA-Lewis. The work had its genesis in the frequency domain acoustic theory developed at Hamilton Standard in the late 1970s. It was found that the method used for near field noise predictions could be adapted as a lifting surface theory for aerodynamic work via the pressure potential technique that was used for both wings and ducted turbomachinery. In the first realization of the theory for propellers, the blade loading was represented in a quasi-vortex lattice form. This was upgraded to true lifting surface loading. Originally, it was believed that a purely linear approach for both aerodynamics and noise would be adequate. However, two sources of nonlinearity in the steady aerodynamics became apparent and were found to be a significant factor at takeoff conditions. The first is related to the fact that the steady axial induced velocity may be of the same order of magnitude as the flight speed and the second is the formation of leading edge vortices which increases lift and redistribute loading. Discovery and properties of prop-fan leading edge vortices were reported in two papers. The Unified AeroAcoustic Program (UAAP) capabilites are demonstrated and the theory verified by comparison with the predi...
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 5
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-17
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 5 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-17 with categories.
An analysis of tone noise propagation through a boundary layer and fuselage scattering effects was derived. This analysis is a three dimensional and the complete wave field is solved by matching analytical expressions for the incident and scattered waves in the outer flow to a numerical solution in the boundary layer flow. The outer wave field is constructed analytically from an incident wave appropriate to the source and a scattered wave in the standard Hankel function form. For the incident wave, an existing function - domain propeller noise radiation theory is used. In the boundary layer region, the wave equation is solved by numerical methods. The theoretical analysis is embodied in a computer program which allows the calculation of correction factors for the fuselage scattering and boundary layer refraction effects. The effects are dependent on boundary layer profile, flight speed, and frequency. Corrections can be derived for any point on the fuselage, including those on the opposite side from the source. The theory was verified using limited cases and by comparing calculations with available measurements from JetStar tests of model prop-fans. For the JetStar model scale, the boundary layer refraction effects produce moderate fuselage pressure reinforcements aft of and near the plane of rotation and significant attenuation forward of the plane of rotation at high flight speeds. At lower flight speeds, the calculated boundary layer effects result in moderate amplification over the fuselage area of interest. Apparent amplification forward of the plane of rotation is a result of effective changes in the source directivity due to boundary layer refraction effects. Full scale effects are calculated to be moderate, providing fuselage pressure amplification of about 5 dB at the peak noise location. Evaluation using available noise measurements was made under high-speed, high-altitude flight conditions. Comparisons of calculations made of free field noise, using a cur...
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 2
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-15
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise Volume 2 written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-15 with categories.
A unified theory for aerodynamics and noise of advanced turboprops is presented. The theory and a computer code developed for evaluation at the shielding benefits that might be expected by an aircraft wing in a wing-mounted propeller installation are presented. Several computed directivity patterns are presented to demonstrate the theory. Recently with the advent of the concept of using the wing of an aircraft for noise shielding, the case of diffraction by a surface in a flow has been given attention. The present analysis is based on the case of diffraction of no flow. By combining a Galilean and a Lorentz transform, the wave equation with a mean flow can be reduced to the ordinary equation. Allowance is also made in the analysis for the case of a swept wing. The same combination of Galilean and Lorentz transforms lead to a problem with no flow but a different sweep. The solution procedures for the cases of leading and trailing edges are basically the same. Two normalizations of the solution are given by the computer program. FORTRAN computer programs are presented with detailed documentation. The output from these programs compares favorably with the results of other investigators. Amiet, R. K. Unspecified Center NAS3-23720; RTOP 535-03-01...
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise
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Author : Donald B. Hanson
language : en
Publisher:
Release Date : 1991
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise written by Donald B. Hanson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aerodynamics categories.
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise
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Author : D. B. Hanson
language : en
Publisher:
Release Date : 1991
Unified Aeroacoustics Analysis For High Speed Turboprop Aerodynamics And Noise written by D. B. Hanson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with categories.
Aeroacoustics Of Flight Vehicles Noise Control
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Author : Harvey H. Hubbard
language : en
Publisher:
Release Date : 1991
Aeroacoustics Of Flight Vehicles Noise Control written by Harvey H. Hubbard and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aerodynamic noise categories.
Aeroacoustics Of Low Mach Number Flows
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Author : Stewart Glegg
language : en
Publisher: Elsevier
Release Date : 2023-09-26
Aeroacoustics Of Low Mach Number Flows written by Stewart Glegg and has been published by Elsevier this book supported file pdf, txt, epub, kindle and other format this book has been release on 2023-09-26 with Technology & Engineering categories.
Aeroacoustics of Low Mach Number Flows: Fundamentals, Analysis and Measurement, Second Edition provides a detailed introduction to sound radiation from subsonic flow over moving surfaces. This phenomenon is the most widespread cause of flow noise in engineering systems, including fan noise, rotor noise, wind turbine noise, boundary layer noise, airframe noise and aircraft noise. This fully updated new edition includes additional problems, illustrations and summary materials to support readers. New content covers Rapid Distortion theory (RDT), boundary layer wall pressure fluctuations, and flow induced sound at surfaces. Themes addressing non-compressible flows have also been added, offering coverage of hydroacoustic as well as aeroacoustic applications. New support materials for this edition include course outlines, problem sets, sample MATLAB codes and experimental data to be found at www.aeroacoustics.net. Addresses, in detail, sound from rotating blades, ducted fans, airframes, boundary layers, and more Presents theory in such a way that it can be used in computational methods and calculating sound levels Includes coverage of different experimental approaches to this subject