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Ribner, H. S. (Herbert S.) 1913-

Overview
Works: 60 works in 110 publications in 1 language and 298 library holdings
Genres: Conference proceedings 
Classifications: TL507, 629.132304
Publication Timeline
Key
Publications about H. S Ribner
Publications by H. S Ribner
Most widely held works by H. S Ribner
Spectra of noise and amplified turbulence emanating from shock-turbulence interaction two scenarios by H. S Ribner( Book )
3 editions published in 1986 in English and held by 81 libraries worldwide
Shock-turbulence interactions in a reacting flow by Institute for Computer Applications in Science and Engineering( Book )
4 editions published in 1992 in English and held by 71 libraries worldwide
This paper addresses a specific reactive-flow configuration, namely, the interaction of a detonation wave with convected homogeneous isotropic weak turbulence (which can be constructed by a Fourier synthesis of small-amplitude shear waves). The effect of chemical heat release on the rms fluctuations downstream of the detonation is presented as a function of Mach number. In addition, for the particular case of the von Karman spectrum, the one- dimensional power spectra of these flow quantities is given
Proceedings by Sonic Boom Symposium( Book )
1 edition published in 1972 in English and held by 11 libraries worldwide
Shock-turbulence interaction and the generation of noise by H. S Ribner( Book )
6 editions published between 1954 and 1955 in English and held by 9 libraries worldwide
The interaction of a convected field of turbulence with a shock wave has been analyzed to yield the modified turbulence, entropy spotiness, and noise generated downstream of the shock. This analysis generalizes the results of Technical Note 2864, which apply to a single spectrum component, to give the shock-interaction effects of a complete turbulence field. The previous report solved the basic gas-dynamic problem, and the present report has added the necessary spectrum analysis
Convection of a pattern of vorticity through a shock wave by H. S Ribner( Book )
6 editions published between 1953 and 1954 in English and held by 9 libraries worldwide
An arbitrary weak spatial distribution of vorticity can be represented in terms of plane sinusoidal shear waves of all orientations and wave lengths (Fourier integral). The analysis treats the passage of a single representative weak shear wave through a plane shock and shows refraction and modification of the shear wave with simultaneous generation of an acoustically intense sound wave. Applications to turbulence and to noise in supersonic wind tunnels are indicated
Spectrum of turbulence in a contracting stream by H. S Ribner( Book )
5 editions published between 1952 and 1953 in English and held by 7 libraries worldwide
The spectrum concept is employed to study the selective effect of a stream contraction on the longitudinal and lateral turbulent velocity fluctuations of the stream. By a consideration of the effect of the stream contraction on a single plane sinusoidal disturbance wave, mathematically not dissimilar to a triply-periodic disturbance treated by G.I. Taylor, the effect on the spectrum tensor of the turbulence and hence on the correlation tensor are determined. Lack of interference between waves follows from the postulation of a low level of turbulence; this and the assumption of an inviscid fluid imply neglect of decay effects. The compressibility of the main stream is taken into account, but the density fluctuations associated with the turbulence is assumed to be negligible; this would be the case if the turbulence originated from wakes and boundary layers in the very low speed portion of the flow. For an axisymmetric contraction and a particular isotropic initial turbulence some explicit results are obtained. The one-dimensional longitudinal spectrum is found to be distorted (as well as reduced in amplitude) with its peak shifted well to the right of the initial position above the zero of the wave-number scale. The selective effect of the contraction on the mean square longitudinal and lateral components of turbulent velocity is found to be given uniquely when the initial turbulence is isotropic, regardless of the details of the spectrum. If the initial spectrum is anisotropic, as, for instance, that produced by a damping screen, then the selective effect is altered. In a crude extension, decay effects outside the scope of the theory are allowed for in first approximation. With this extension, a comparison with experiment is made of the selective effect on turbulent intensity where the estimated decay effects are comparable with the contraction effects
Eddy mach wave noise from a simplied model of a supersonic mixing layer by H. S Ribner( Book )
2 editions published in 1969 in English and held by 6 libraries worldwide
Refraction of sound by jet flow or jet temperature by Canada( Book )
2 editions published in 1965 in English and held by 6 libraries worldwide
The heart-shaped pattern of subsonic jet noise normally peaks somewhere between 15 degrees and 45 degrees from the axis, depending on conditions, falling off sharply as the axis is approached. Conflicting explanations of this directivity pattern appear in the literature. The present investigation suggests that the deep cleft in the pattern can be attributed mainly to refraction of the sound out of the jet by the velocity and temperature fields. The evidence lies in measurements made of the sound field of a harmonic 'point' source placed within a 3/4 in. dia. air jet. The source is the orifice of a tube about 1/16 in. i.d. driven through a conical coupling by a horn-type loudspeaker driver; this radiates sound essentially omnidirectionally up to about 15,000 cps. The experiment established the formation of an axial intensity minimum, which appears to be mainly due to refraction. The depth of the refraction valley increases with jet velocity, jet temperature, and sound frequency; a depth corresponding to an intensity reduction of the order of 35 dB is attained at M = 0.9 for 3000 cps. (Author)
Subjective loudness of sonic-boom : N-wave and minimized ('low-boom') signatures by University of Toronto( Book )
5 editions published in 1977 in English and held by 6 libraries worldwide
A loudspeaker-driven simulation booth with extended rise-time capability (down to 0.22 ms) has been used for subjective loudness tests of sonic booms. Test series I compared N-waves over a range of 0.22 to 10 ms rise time, 100 to 250 ms duration and 0.5 to 2.0 psf (24 to 96 N/sq m) peak overpressure. In one sequence, tradeoff between rise time and overpressure was measured for equal loudness; in another, the tradeoff between duration and overpressure. For equal loudness 10 ms rise time required 8 dB higher overpressure than for 1 ms rise time. Duration had little effect in the range 100 to 200 ms but at 250 ms noticeably enhanced the loudness. These results confirm those measured by Shepherd and Sutherland, made at 1 ms rise time and above (except for the anomalous enhancement at 250 ms duration), and extend the measurements down to 0.22 ms. There is also good agreement with theoretical predictions (Johnson-Robinson, Zepler-Harel methods) except for the 10 ms rise time and 250 ms duration cases
Supersonic turns without superbooms by H. S Ribner( Book )
2 editions published in 1972 in English and held by 6 libraries worldwide
An experimental investigation of turbulence-excited panel vibration and noise (boundary-layer noise) by M. Y El Baroudi( Book )
2 editions published in 1963 in English and held by 6 libraries worldwide
A study is made of the flexural motion and noise generated by 11 x 11 in. steel panels flush mounted in the wall of a turbulent flow channel. The mean square exciting pressure fluctuation at the wall, its spectral density, and two- point correlations of the pressure were measured with the use of pinhole microphones. The flexural response of sample panels was studied by correlation techniques. The calculated relief plot of correlation shows qualitative agreement with the experimental results
Quadrupole Correlations Governing the Pattern of Jet Noise by H. S Ribner( Book )
3 editions published in 1967 in English and held by 5 libraries worldwide
The effects of convection and refraction dominate the heart-shaped pattern of jet noise. These can be corrected out to yield the 'basic directivity' of the eddy noise generators. The observed quasi-ellipsoidal pattern was predicted by Ribner (1963, 1964) in a variant of the Lighthill theory, postulating isotropic turbulence superposed on a mean shear flow. This had the feature of dealing with the joint effects of the quadrupoles without displaying them individually. The paper reformulates the theory so as to calculate the relative contributions of the different quadrupole self- and cross-correlations to the sound emitted in a given direction. Spectra are also discussed, following the earlier work. Finally, the predictions are shown to be compatible with recent experimental results. Of the 36 possible quadrupole correlations only 9 yield distinct nonzero contributions to the axisymmetric noise pattern of a round jet. The individual directional patterns have either 2 or 4 lobes, but they combine to yield a quasi-ellipsoidal overall pattern ('basic' directivity before convection or refraction are allowed for). This is compounded of partial patterns called 'self-noise' and 'shear-noise'. (Author)
Propellers in yaw by H. S Ribner( Book )
3 editions published in 1943 in English and held by 5 libraries worldwide
Summary: It was realized as early as 1909 that a propeller in yaw develops a side force like that of a fin. In 1917, R.G. Harris expressed this force in terms of the torque coefficient for the unyawed propeller. Of several attempts to express the side force directly in terms of the shape of the blades, however, none has been completely satisfactory. An analysis that incorporates induction effects not adequately covered in previous work and that gives good agreement with experiment over a wide range of operating conditions is presented herein. The present analysis shows that the fin analogy may be extended to the form of the side-force expression and that the effective fin area may be taken as the projected side area of the propeller. The effective aspect ratio is of the order of 8 and the appropriate dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixed-pitch propeller, accounts for most of the variation of side force with advance-diameter ration V/nD
Field of flow about a jet and effect of jets on stability of jet-propelled airplanes by H. S Ribner( Book )
4 editions published in 1946 in English and held by 5 libraries worldwide
Summary: The flow inclination induced outside cold and hot propulsive jets by the turbulent spreading has been derived. Certain simplifying assumptions were employed and the region near the orifice was not treated. The effect of jet temperature on the flow inclination was found to be small when the thrust coefficient is used as the criterion for similitude. The deflection of a jet due to angle of attack has been derived and found to be appreciable but small for normal flight conditions with small normal accelerations. The average jet-induced downwash over a tail plane has been obtained in terms of the geometry of the jet-tail configuration. These results have been applied to the estimation of the effect of the jets on the static longitudinal stability and trim of jet-propelled airplanes
Formulas for propellers in yaw and charts on the side-force derivative by H. S Ribner( Book )
3 editions published in 1943 in English and held by 5 libraries worldwide
Summary: General formulas are given for propellers for the rate of change of side-force coefficient with angle of yaw and for the rate of change of pitching-moment coefficient with angle of yaw. Charts of the side-force derivative are given for two propellers of different plan form. The charts cover solidities of two to six blades and single and dual rotation. The blade angles range from 15° or 20° to 60°. The equations, and the charts computed from the equations, are based on an unpublished analysis, which incorporates factors not adequately covered in previously published work and gives good agreement with experiment over a wide range of operating conditions. A study of the equations indicates that they are consistent with the following physical interpretation: In developing side force, the propeller acts like a fin of which the area is the projected side area of the propeller, the effective aspect ratio is of the order of 8, and the effective dynamic pressure is roughly that at the propeller disk as augmented by the inflow. The variation of the inflow velocity, for a fixed-pitch propeller, accounts for most of the variation of side force with advance-diameter ratio. The charts may be applied to obtain the rate of change of normal-force coefficient with angle of attack of the axis of rotation if proper account is taken of the upwash or downwash from the wing
A deterministic model of sonic boom propagation through a turbulent atmosphere by B. H. K Lee( Book )
4 editions published in 1972 in English and held by 4 libraries worldwide
The propagation of a weak normal shock wave through a turbulent atmosphere is studied in terms of an idealized model. The turbulent field is assumed to be weak and represented by the superposition of two inclined shear waves of opposite inclination to the mean flow. The resulting flow is of a cellular nature. The cells are rectangular in shape and the sense of rotation of the flow alternates from cell to cell. If the angles made by the normal of the incident shear waves with the direction of the mean flow are greater than some critical value an exponentially decaying pressure wave is generated behind the shock. 'Spiked' or rounded' waveforms are obtained by adding or subtracting this pressure wave from the steady state pressure field. An illustrative example for a mean flow Mach number of 1.0005 is considered. (Author)
AERODYNAMICALLY GENERATED SOUND ( Book )
4 editions published between 1964 and 1979 in English and held by 4 libraries worldwide
The research accomplishments of the project are summarized. A study of surface motion in turbulence-induced panel vibration demonstrated that panel motion consists of running waves forced by the convected pressure field superposed on a more irregular pattern. Turbulent structure in the transition region, (4.5 to 8 diams downstream of the nozzle) of a 4-in. low-speed jet was investigated with the aim of relating the turbulence to the noise generating features of such a jet. Progress has been made in improving the accuracy of the hot-wire and time-delay correlator instrumentation, and timing, gate, and relay circuits were developed to semi-automate data processing. Constanttemperature hot-wires were found to obey a sine law quite accurately over a wide range when inclined to the stream. An aerofoil probe for measuring the transverse component of turbulence was also developed. Lastly, an anomaly in the directivity pattern of jet noise was resolved. Measurements in an anechoic room with a harmonic point sound source placed in an air jet indicated that the sound appears to be refracted away from the jet axis. This gives a marked dimple in the sound directivity pattern very similar to the dimple found with random jet noise. (Author)
A transonic propeller of triangular plan form : an extension by H. S Ribner( Book )
3 editions published in 1978 in English and held by 4 libraries worldwide
Damping in roll of cruciform and some related delta wings at supersonic speeds by H. S Ribner( Book )
1 edition published in 1951 in English and held by 3 libraries worldwide
The damping in roll of cruciform delta wings in supersonic flow has been evaluated by means of small-disturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known two-dimensional results for rotating multibladed laminae have been applied to obtain the loading when the number of panels is changed from four to an arbitrary number, under the restriction of low aspect ratio; the damping in roll has been determined explicitly for three panels. Finally, the damping for an inifinite number of panels has been evaluated without restriction as to aspect ratio or Mach number
Acoustic energy flux from shock-turbulence interaction by Herbert S Ribner( Book )
3 editions published in 1967 in English and held by 3 libraries worldwide
The analysis of the sound field generated by the passage of isotropic turbulence through a shock of finite strength (Ribner, 1953, 1954) was extended to provide the flux of acoustic energy. The energy flux varies almost linearly with shock density ratio, reaching a maximum at infinite Mach number of 0.062 of the flux of turbulence kinetic energy. Direct comparison with a result obtained by Lighthill (1953) is misleading. His energy relations, reckoned relative to a frame moving with the fluid, must be converted to the shock-fixed frame used in this report. The converted results of his theory (weak shocks) and the results of the author's theory (arbitrary shocks) appear to show a similar asymptotic behavior for vanishing shock strength; they diverge with increasing shock strength. (Author)
 
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Alternative Names
Ribner, Herbert S.
Ribner, Herbert S., 1913-
Languages
English (66)
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