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

Overview
Works: 52 works in 172 publications in 1 language and 505 library holdings
Genres: Conference papers and proceedings 
Roles: Author
Classifications: TL521, 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 )
5 editions published between 1986 and 1987 in English and held by 90 libraries worldwide
An extension of the Lighthill theory of jet noise to encompass refraction and shielding by H. S Ribner( Book )
3 editions published in 1995 in English and held by 78 libraries worldwide
Theory of two-point correlations of jet noise by H. S Ribner( Book )
5 editions published between 1976 and 1977 in English and held by 23 libraries worldwide
Proceedings by Sonic Boom Symposium( Book )
1 edition published in 1972 in English and held by 11 libraries worldwide
A Transonic propeller of triangular plan form by H. S Ribner( Book )
5 editions published between 1947 and 1978 in English and held by 10 libraries worldwide
An isosceles triangle twisted into a screw surface about its axis is proposed as a propeller for transonic flight speeds. The purpose is to attanin the drag reduction associated with large sweepback in a structurally practicable configuration. A mathematical theory for such a propeller is presented. Calculations taking account of wave and skin-friction drag indicate a net efficiency of the order of 80 percent at Mach nuber of 1.1. A 12-foot propeller is estimated to be able to absorb 18,500 brake horsepower at 840 miles per hour at sea level
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 10 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
Propellers in yaw by H. S Ribner( Book )
8 editions published between 1943 and 1945 in English and held by 10 libraries worldwide
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
A deterministic model of sonic boom propagation through a turbulent atmosphere by B. H. K Lee( Book )
6 editions published in 1972 in English and held by 10 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)
Formulas for propellers in yaw and charts on the side-force derivative by H. S Ribner( Book )
8 editions published between 1943 and 1945 in English and held by 10 libraries worldwide
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 degrees or 20 degrees to 60 degrees
Spectrum of turbulence in a contracting stream by H. S Ribner( Book )
6 editions published between 1952 and 1953 in English and held by 10 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
An experimental investigation of turbulence-excited panel vibration and noise (boundary-layer noise) by M. Y El Baroudi( Book )
6 editions published in 1963 in English and Undetermined and held by 9 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
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
Stability derivatives of triangular wings at supersonic speeds by H. S Ribner( Book )
7 editions published between 1948 and 1950 in English and held by 8 libraries worldwide
The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds, given in NACA TN No. l423, is extended to apply to triangular wings having large vertex angles and traveling at supersonic speeds. The lift, rolling moment due to siderlip, and damping in roll and pitch for this more general case have been treated elsewhere on the basis of the theory of small disturbances
Acoustic energy flux from shock-turbulence interaction by H. S Ribner( Book )
4 editions published in 1967 in English and held by 7 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)
Quadrupole Correlations Governing the Pattern of Jet Noise by H. S Ribner( Book )
4 editions published in 1967 in English and held by 7 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)
Effect of slipstream rotation in producing asymmetric forces on a fuselage by H. S Ribner( Book )
2 editions published in 1947 in English and held by 7 libraries worldwide
An approximate theory of the effect of slipstream rotation on the forces on a fuselage without a wing represents the slipstream rotation by the flow about a vortex alined with the longitudinal axix. This configuration gives rise to a lateral force and yawing moment in ptich or a normal force and pitching moment in yaw. The forces are proportional to angle inclination and to slipstream rotation as measured by the ratio of propeller torque to the square of the diameters
Eddy mach wave noise from a simplied model of a supersonic mixing layer by H. S Ribner( Book )
4 editions published in 1969 in English and held by 7 libraries worldwide
A simplified flow model is presented for simulating features of noise generation by supersonic jets and rockets. 'Eddy Mach waves' appear as a consequence of balancing internal and external pressures, and noise power may be estimated. Specifically, the turbulent mixing layer of a supersonic jet is modeled as a layer of two-dimensional square 'eddies'; this separates the main flow from fluid at rest and moves at an intermediate speed. (In an improved model the square eddies are replaced by a turbulent flow layer constrained by plane interfaces). The initially plane interfaces, because of unopposed internal pressures, will ripple slightly such that Mach waves arise and effect a pressure balance. The Mach wave noise pattern is readily calculated as well as the acoustic energy flux. (Author)
Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges by Frank S Malvestuto( Book )
4 editions published in 1949 in English and held by 6 libraries worldwide
On the basis of linearized supersonic-flow theory, calculations are made for the lift and damping in roll of a series of thin sweptback wings of arbitrary taper and sweep. Results are applicable to wings with streamwise tips and for a range of supersonic speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and from the trailing edge of the root section. A further limitation is that the tip Mach lines may not intersect on the wing
Field of flow about a jet and effect of jets on stability of jet-propelled airplanes by H. S Ribner( Book )
6 editions published in 1946 in English and held by 6 libraries worldwide
A theoretical investigation was conducted on jet-induced flow deviation. Analysis is given of flow inclination induced outside cold and hot jets and jet deflection caused by angle of attack. Applications to computation of effects of jet on longitudinal stability and trim are explained. Effect of jet temperature on flow inclination was found small when thrust coefficient is used as criterion for similitude. The average jet-induced downwash over tail plane was obtained geometrically
Damping in roll of cruciform and some related delta wings at supersonic speeds by H. S Ribner( Book )
4 editions published in 1951 in English and held by 6 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
 
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Alternative Names
Ribner, Herbert S.
Ribner, Herbert S. 1913-
Languages
English (99)
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