WorldCat Identities

Strahle, Warren C.

Overview
Works: 77 works in 133 publications in 1 language and 714 library holdings
Genres: Conference papers and proceedings  Handbooks and manuals 
Roles: Author
Publication Timeline
.
Most widely held works by Warren C Strahle
Aeroacoustics : technical papers from AIAA 2nd Aero-acoustics Conference, March 1975, subsequently revised for this volume by AIAA Aero-Acoustics Specialists Conference( Book )

6 editions published in 1976 in English and held by 229 WorldCat member libraries worldwide

"The papers in this volume deal with recent research into acoustic-wave propagation through the atmosphere and progress in aeroacoustic instrumentation, facilities, and test techniques. Topics include the propagation of aircraft noise over long distances in the lower atmosphere, measured effects of turbulence on the rise time of a weak shock, sound scattering from atmospheric turbulence, saturation effects associated with sound propagation in a turbulent medium, and a computer model of the lightning-thunder process. Other papers discuss the development of a computer system for aircraft noise prediction; aircraft flyover noise measurements; and theories and methods for the prediction of ground effects on aircraft noise propagation, for the prediction of airframe aerodynamic noise, for turbine noise prediction, and for combustion noise prediction. Attention is also given to the use of Hartmann generators as sources of high-intensity sound in a large absorption flow-duct facility, an outdoor jet noise facility, factors in the design and performance of free-jet acoustic wind tunnels, and the use of a laser shadowgraph for jet noise diagnosis."--Publisher description
An introduction to combustion by Warren C Strahle( Book )

11 editions published between 1993 and 1996 in English and held by 181 WorldCat member libraries worldwide

Combustion noise prediction, entropy/vorticity effects( Book )

3 editions published in 1979 in English and held by 61 WorldCat member libraries worldwide

An experimental and theoretical program was conducted to see if entropy noise and vorticity-nozzle interaction noise, as well as direct combustion noise, could be isolated in gas turbine combustor tests. Moreover, a unified correlation, with a rational theoretical basis, was developed for direct noise from combustor rig tests. It was found that (a) vorticity noise was at least as large as combustion noise; (b) entropy noise is minor but is large only at low frequency; (c) all noise sources are coherent with each other over various frequency ranges; (d) with a choked nozzle termination the nose is higher frequency (approximately 2000 Hz) than heretofore believed; (e) some other unexplained noise source contaminated the results at low frequency; and (f) the diffuser used caused additional coherent noise, probably through the vorticity source. A method for accounting for the vorticity and entropy sources in combustor rig tests was indicated. (Author)
Aeroacoustics, fan noise and control, duct acoustics, rotor noise : technical papers from AIAA 2nd Aero-acoustics Conference, March 1975, subsequently revised for this volume by AIAA Aero-acoustics Conference( Book )

5 editions published in 1976 in English and held by 40 WorldCat member libraries worldwide

"The recent progress in duct acoustic research is reflected by fourteen papers which cover essentially the areas of linear duct acoustics, the characteristics of absorbent materials, and nonlinear duct acoustics. With respect to propagation in ducts, emphasis is placed on computational methods aimed at attaining effective economical modeling of propagation in variable-geometry and in hard-wall or soft-wall ducts. Computational methods developed to reduce computer processing and storage requirements are outlined, along with a wave envelope technique for reducing processing and storage needs. The latter technique is applied to the optimum segmented acoustic duct linear design. A finite difference technique is used in combination with conformal mapping to compute the optimum multisection duct linear design."--Publisher description
Aeroacoustics, STOL noise, airframe and airfoil noise : technical papers from AIAA 2nd Aero-acoustics Conference, March 1975, subsequently revised for this volume by AIAA Aero-acoustics Conference( Book )

3 editions published in 1976 in English and held by 36 WorldCat member libraries worldwide

"The papers in this volume reflect the progress in aeroacoustic research which has been made in the field of VTOL and V/STOL aircraft noise. The research was directed mainly at developing better methods for predicting noise generation and propagation, at determining the effects of pressure fluctuations on surfaces and interior noise, and at developing noise abatement techniques. Among the topics covered are: scrubbing noise of externally blown flaps; propulsive-lift noise of an upper-surface-blown flap configuration; the aeroacoustic characteristics of model slot nozzles with straight flaps; fluctuating pressures on aircraft wing and flap surfaces associated with powered-lift systems; acoustic characteristics of a large upper-surface-blown configuration with turbofan engines; the effect of forward speed on jet/flap interaction noise; and airframe noise in the far field."--Publisher description
Aeroacoustics, jet noise, combustion and core engine noise : technical papers from AIAA 2nd Aero-acoustics Conference, March 1975, subsequently revised for this volume by Ira R Schwartz( Book )

5 editions published in 1976 in English and held by 26 WorldCat member libraries worldwide

The computation of oblique shock wave characteristics for real gases by Warren C Strahle( Book )

2 editions published in 1961 in English and held by 7 WorldCat member libraries worldwide

A method is presented whereby oblique shock wave data for real gases may be readily obtained from real gas normal shock wave data corresponding to the same upstream thermodynamic state. Although such solutions are well known for perfect gases there appears to be no method available at this time to account for real gas effects. This method is only useful when the flow deflection angle is the specified parameter instead of the wave inclination angle. There is no restriction to any gas com position since the physics of the problem are completely contained in the normal shock characteristics. It is expected that primary use of this method will be found in the study of vehicles for entry into planetary atmospheres. Because of the present uncertainty of the characteristics of any of the planetary atmospheres it is not economically justifiable to compute oblique shock charts for every conceivable model atmosphere. However, to even begin consideration of an entry vehicle requires that some normal shock computations be made. (Author)
A theoretical study of unsteady droplet burning : transients and periodic solutions by Warren C Strahle( )

5 editions published between 1963 and 1964 in English and held by 7 WorldCat member libraries worldwide

The thermodynamic properties and shock-wave characteristics of a model Venus atmosphere by Warren C Strahle( Book )

2 editions published in 1962 in English and held by 6 WorldCat member libraries worldwide

A model for the atmosphere of Venus is developed which may be useful for design studies of early atmospheric-entry vehicles and for wind-tunnel simulation application. This atmosphere, derived from many questionable assumptions and scant experimental data, consists of 85% carbon dioxide and 15% nitrogen by volume. The thermodynamic properties of the derived atmospheric composition are presented over the temperaturepressure range of 150 to 24,000 K and 1/10,000 to 100 atm. To further assist in aerodynamic entry calculations, normal-shock-wave characteristics of such an atmosphere are also presented. The fact that nitrogen is present has important consequences in the thermodynamic properties and electron concentrations over the full temperature and pressure range. The effects are of the order of the percentage of nitrogen addition to pure carbon dioxide. A graphical method of obtaining oblique-shock-wave data and a method of obtaining electron concentrations at low temperatures are included as appendixes. (Author)
Aeroacoustics : technical papers from AIAA 2nd Aero-Acoustics Conference, March 1975, subsequently revised for this volume( Book )

1 edition published in 1976 in English and held by 4 WorldCat member libraries worldwide

Combustion generated noise in turbopropulsion systems( Book )

4 editions published between 1973 and 1975 in English and held by 4 WorldCat member libraries worldwide

Continuation of experimental and theoretical work on the problem of combustion generated noise in turbopropulsion systems is presented. Tasks completed during the current period have been (a) experimental and theoretical correlation of noise power and spectra from open premixed flames of propane, propylene, ethylene and acetylene-air, (b) crosscorrelation of C2 emission with the far field acoustic pressure, and (c) experimental and theoretical investigation of ducting effects upon the noise radiating capability of the flame. The noise radiation from simple flame types is now understood with sufficient theoretical and experimental detail that estimates may be made for combustion noise in turbopropulsion systems. (Modified author abstract)
Combustion noise by Warren C Strahle( Book )

4 editions published in 1977 in English and Undetermined and held by 4 WorldCat member libraries worldwide

Heterogeneous diffusion flame stabilization by Warren C Strahle( Book )

3 editions published in 1987 in English and held by 3 WorldCat member libraries worldwide

Analytical modelling and several experimental diagnostics were applied to an experimental flow in a two-dimensional subsonic windtunnel with a backward facing step and provision for injection of inerts and combustibles through the porous floor behind the step. The analytical techniques were based on a two equation modeling of turbulence with several variants of near wall models and numerical approaches. Conventional experimental techniques, where applicable in the cold flow, included hot film and pitot and anemometry. Laser - based diagnostics in the cold and hot flows for velocity and species concentration measurements (both mean and instantaneous) included laser velocimetry in two components and Rayleigh molecular scattering. Major findings in this complex turbulent flow with chemical reactions were a) there was a general agreement between analysis and experiment in cold flow both with and without wall injection, b) this agreement occurred at the the most detailed level of turbulent shear stress and mass transport, c) in hot flow there was acceptable agreement as to the gross features of the mean flow field, but some theoretical details, such as reattachment length, went counter to experimental results
Audible and Ultrasonic Acoustic Emissions from Composite Solid Propellants( Book )

3 editions published between 1975 and 1977 in English and held by 3 WorldCat member libraries worldwide

The audible and ultrasonic acoustic emissions from deflagrating composite solid propellants were monitored and analyzed to evaluate their potential use as diagnostics of the combustion and as a means for the study of fundamental burning processes. A family of composite HTPB-AP propellants were tested which include a range of AP particle sizes, aluminized and nonaluminized formulations, the effect of the addition of a catalyst, and the presence of an AFCAM aluminum coating. For the audible emissions, the frequency behavior in the 0-10 kHz range can be explained by assuming the gas phase reaction time primarily controls the oscillating frequency. The combustion noise efficiency, cannot be explained by the theories put forth, so the physical makeup of the noise source is presently unknown. Analysis of the ultrasonic emission spectra indicates that there are no distinct spectral features which can be used to identify a particular propellant by its acoustic signature. The rms emission levels, however, can be used as a reliable, nonintrusive means for detecting flaws in the propellant, identifying bad burns, and measuring burn rates. The overall level increases with increasing burn rate and chamber pressure and decreasing particle size. (Author)
Aeroacoustics: STOL noise : airframe and airfoil noise : technical papers from AIAA 2nd Aero-Acoustics conference : (Hampton - Va.), March 1975( Book )

2 editions published in 1976 in English and held by 3 WorldCat member libraries worldwide

Rocket Research at Georgia Tech( Book )

3 editions published between 1979 and 1981 in English and held by 3 WorldCat member libraries worldwide

Progress is reported on four distinct projects which are administered as a group. The individual projects are identified as tasks and reported on separately. A summary for each task follows: Task I. Work concerned improvement and application of the impedance tube method for measurement of the presure-coupled combustion response of solid propellants and measurement of the bulk damping in the product flow. Improvements included increaed sites and amplitude range of pressure measurements; increased capacity of the data acquisition system; and a modified, more rapid data reduction program. Admittances and bulk loss coefficients of nonaluminized and aluminized propellants were measured over a range of frequencies. Task II. Studies were continued on external burning using an axisymmetric model at Mach 3. Tests with actual combustion of radially and axially injected hydrogen are then reported. Outstanding performance values with significant base drag reduction is shown for injection and burning directly in the near-wake (base burning). Task III. Investigations continued of the accumulation processes of aluminum on the propellant burning surface that lead to formation of agglomerate droplets, the size of which dominates aluminum combustion. Task IV. Experimental and analytical studies were continued on the subject of turbulence-induced pressure fluctuations in a rocket-like cavity. A new theory was constructed for the generation of pressure disturbances by the turbulence. Undeniable separation has been achieved between propagational and local pressure fluctuations, and the agreement between theory and experiment are adequate
Acoustic signature from flames as a combustion diagnostic tool by Warren C Strahle( Book )

3 editions published in 1983 in English and held by 2 WorldCat member libraries worldwide

A program was conducted to investigate the feasibility of using the combustion noise acoustic output as a non-intrusive diagnostic of some details of the combustion process. Investigated were an open premixed turbulent jet flame and a gas turbine combustor converted to run on propane. The analysis links the acoustic pressure fluctuations to the distribution of heat release rate fluctuations. Measurement of the sound field, yields in principle, the heat release rate fluctuation field. It was found, however, that the analytical methods for this inverse problem are too sensitive to small experimental uncertainties. Consequently, it appears that the method is not, in general feasible
Fractal image compression of Rayleigh, Raman, LIF, and LDV data in turbulent reacting flows by Warren C Strahle( Book )

4 editions published between 1990 and 1991 in English and held by 2 WorldCat member libraries worldwide

Fractal geometry analysis methods, analytical modeling and several experimental diagnostics were applied to an experimental reacting flow in a two- dimensional subsonic windtunnel with a backward facing step and provision for injection of inerts and combustibles through the porous floor behind the step. Experiments used laser velocimetry and Raman spectroscopy measurements for two components of the mean and fluctuating velocity and the local nitrogen concentration, which was found in this flow to be an accurate temperature sensor. The fuel used was hydrogen diluted with argon or nitrogen. Fractal geometry yielded a new nonlinear adaptive filter and an interpolation method for improving the statistics of sparsely separated data points. Analytical modeling was improved over from a prior program, and a two equation turbulent model now reproduces many of the observed features of the reacting flow
Experiments and Analysis Related to External Burning for Propulsion( Book )

2 editions published between 1976 and 1977 in English and held by 1 WorldCat member library worldwide

An experimental study of base flow for a 2.25 inch diameter projectile at Mach 3 with and without simulated external burning disturbances is reported. Base pressure and wake structure results from systematic variations in axisymmetric external compression show that substantial base thrust can be produced and that the pressure and length scales of the external compression are imposed on the near wake. Measurements with comparable axisymmetric and asymmetric compression contours show that peripherial gradients reduce the base pressure rise. Furthermore, relatively large changes in the near wake length scales and a slight reduction in the base pressure occur when the solid-blockage effects of discrete radial fuel jets are modeled with pegs mounted near the base of the test projectile. (Author)
 
moreShow More Titles
fewerShow Fewer Titles
Audience Level
0
Audience Level
1
  Kids General Special  
Audience level: 0.66 (from 0.47 for Heterogene ... to 0.99 for Rocket Res ...)

Alternative Names
Strahle, W. C.

Strahle, W. C. (Warren C.)

Languages
English (72)