Download or read book Aeroacoustics of Low Mach Number Flows written by Stewart Glegg and published by Academic Press. This book was released on 2017-02-15 with total page 554 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroacoustics of Low Mach Number Flows: Fundamentals, Analysis, and Measurement provides a comprehensive treatment of sound radiation from subsonic flow over moving surfaces, which is the most widespread cause of flow noise in engineering systems. This includes fan noise, rotor noise, wind turbine noise, boundary layer noise, and aircraft noise. Beginning with fluid dynamics, the fundamental equations of aeroacoustics are derived and the key methods of solution are explained, focusing both on the necessary mathematics and physics. Fundamentals of turbulence and turbulent flows, experimental methods and numerous applications are also covered. The book is an ideal source of information on aeroacoustics for researchers and graduate students in engineering, physics, or applied math, as well as for engineers working in this field. Supplementary material for this book is provided by the authors on the website www.aeroacoustics.net. The website provides educational content designed to help students and researchers in understanding some of the principles and applications of aeroacoustics, and includes example problems, data, sample codes, course plans and errata. The website is continuously being reviewed and added to. Explains the key theoretical tools of aeroacoustics, from Lighthill’s analogy to the Ffowcs Williams and Hawkings equation Provides detailed coverage of sound from lifting surfaces, boundary layers, rotating blades, ducted fans and more Presents the fundamentals of sound measurement and aeroacoustic wind tunnel testing

Download or read book Measurements of the Mach Number and Pressure on the Afterbody of a Blunt nosed Model in Free Flight at Mach Numbers from 6 5 to 14 written by Simon C. Sommer and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Mach Number Up to 0 34 and Reynolds Number Up to 8 000 000 on the Maximum Lift Coefficient of a Wing of NACA 66 series Airfoil Sections written by G. Chester Furlong and published by . This book was released on 1950 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.

Download or read book Effects of Subsonic Mach Number on the Forces and Pressure Distributions on Four NACA 64A series Airfoil Sections at Angles of Attack as High as 28 Degrees written by Louis S. Stivers and published by . This book was released on 1954 with total page 676 pages. Available in PDF, EPUB and Kindle. Book excerpt: A region of slight compression, heretofore undescribed, was established within the local supersonic region on each of the airfoil sections near the leading edge in place of an expected expansion. This leading edge compression region was formed just downstream of the abrupt.

Download or read book Analysis of Wind tunnel Tests to a Mach Number of 0 90 of a Four engine Propeller driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 written by George G. Edwards and published by . This book was released on 1956 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.

Download or read book Experimental Investigation of a Hypersonic Glider Configuration at a Mach Number of 6 and at Full scale Reynolds Numbers written by Alvin Seiff and published by . This book was released on 1961 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers written by Richard D. Samuels and published by . This book was released on 1967 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Mach Number and Wall temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5 written by Thorval Tendeland and published by . This book was released on 1959 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The heat-transfer data obtained from the model were found to correlate when the T' method of Sommer and Short was used. The increase in turbulent heat-transfer rate with a reduction in wall to free-stream temperature ratio was of the same order of magnitude as has been found for the turbulent skin-friction coefficient.

Download or read book A Study of the Simulation of Flow with Free stream Mach Number 1 in a Choked Wind Tunnel written by John R. Spreiter and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The degree to which experimental results obtained under choking conditions in a wind tunnel with solid walls simulate those associated with an unbounded flow with free-stream Mach number 1 is investigated for the cases of two-dimensional and axisymmetric flows. It is found that a close resemblance does indeed exist in the vicinity of the body, and that the results obtained in this way are generally at least as accurate as those obtained in a transonic wind tunnel with partly open test section. Some of the results indicate, however, that substantial interference effects, particularly those of the wave reflection type, may be encountered under certain conditions, both in choked wind tunnels and in transonic wind tunnels, and that the reduction of these interference effects to acceptable limits may require the use of models of unusually small size.

Download or read book Friction and Pressure Drag of Boundary Layer Diverter Systems at Mach Number of 3 0 written by Leonard E. Stitt and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Skin Friction Measurements at a Mach Number of Three and Momentum Thickness Reynolds Numbers Up to a Half Million written by Anthony W. Fiore and published by . This book was released on 1980 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface shear stress measurements were made in the Flight Dynamics Laboratory's M=3 High Reynolds Number wind tunnel. The primary purpose of this research was to make shear stress measurements at very high Reynolds numbers for near adiabatic wall and zero pressure gradient conditions. The results are presented as the local skin friction coefficient versus both the momentum thickness and the length Reynolds number. The investigation was conducted on the nozzle wall at a nominal Mach number of three over the Reynolds number range of 20,000

Download or read book Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total Base and Skin friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag written by August F. Bromm and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Boundary layer Displacement Effects in Air at Mach Numbers of 6 8 and 9 6 written by Mitchel H. Bertram and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Mach Number Leading Edge Bluntness and Sweep on Boundary layer Transition on a Flat Plate written by Don W. Jillie and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Drag Due to Lift at Mach Numbers Up to 2 0 written by Edward C. Polhamus and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Performance of Compressor Blade Cascades at High Mach Numbers written by Seymour M. Bogdonoff and published by . This book was released on 1947 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of a Mixed compression Axisymmetric Inlet System at Mach Numbers 0 6 to 3 5 written by Donald B. Smeltzer and published by . This book was released on 1970 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt: