Ribner, H. S. (Herbert S.) 1913
Most widely held works by
H. S Ribner
Spectra of noise and amplified turbulence emanating from shockturbulence 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 twopoint 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 skinfriction drag indicate a net efficiency of the order of 80 percent at Mach nuber of 1.1. A 12foot 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 sideforce 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 fixedpitch propeller, accounts for most of the variation of side force with advancediameter 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 sideforce 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 sideforce coefficient with angle of yaw and for the rate of change of pitchingmoment coefficient with angle of yaw. Charts of the sideforce 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 triplyperiodic 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 onedimensional 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 wavenumber 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 turbulenceexcited panel vibration and noise (boundarylayer 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
Shockturbulence 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 shockinteraction effects of a complete turbulence field. The previous report solved the basic gasdynamic 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 lowaspectratio 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 shockturbulence 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 shockfixed 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 heartshaped pattern of jet noise. These can be corrected out to yield the 'basic directivity' of the eddy noise generators. The observed quasiellipsoidal 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 crosscorrelations 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 quasiellipsoidal overall pattern ('basic' directivity before convection or refraction are allowed for). This is compounded of partial patterns called 'selfnoise' and 'shearnoise'. (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 twodimensional 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 supersonicflow 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 jetpropelled 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 jetinduced 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 jetinduced 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 smalldisturbance (linearized) wing theory; both subsonic and supersonic component stream velocities normal to the leading edges have been considered. In addition, some known twodimensional 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
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