skip to content

Ribner, Herbert S.

Overview
Works: 35 works in 73 publications in 1 language and 219 library holdings
Roles: Author
Classifications: TL521, 629.132305
Publication Timeline
Key
Publications about Herbert S Ribner
Publications by Herbert S Ribner
Most widely held works by Herbert S Ribner
An extension of the Lighthill theory of jet noise to encompass refraction and shielding by H. S Ribner( Book )
1 edition published in 1995 in English and held by 77 libraries worldwide
Theory of two-point correlations of jet noise by H. S Ribner( Book )
4 editions published in 1976 in English and held by 22 libraries worldwide
Stability derivatives of triangular wings at supersonic speeds by H. S Ribner( Book )
9 editions published between 1947 and 1950 in English and held by 12 libraries worldwide
Low-aspect-ratio wings having triangular plan forms are treated on the assumption that the flow potentials in planes at right angles to the long axis of the airfoils are similar to the corresponding two-dimensional potentials. Pressure distributions caused by downward acceleration, pitching, rolling, sideslipping, and yawing are obtained for wings with and without dihedral. The stability derivatives calculated from these distributions are expected to apply at about subsonic and supersonic speeds, with the exception of the transonic and supersonic speeds, with the exception of the transonic region, up to a limiting speed at which the triangle is no longer compared with the Mach cone from its vertex
Formulas for propellers in yaw and charts on the side-force derivative by H. S Ribner( Book )
5 editions published between 1943 and 1945 in English and held by 6 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° 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 The equations, and the charts computed from the equations, are based on an unpublished analysis, which incorporates factors not adequately covered in previously published work and gives good agreement with experiment over a wide range of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
Propellers in yaw by H. S Ribner( Book )
5 editions published between 1943 and 1945 in English and held by 6 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 Transonic propeller of triangular plan form by H. S Ribner( Book )
2 editions published in 1947 in English and held by 5 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
Supersonic turns without superbooms by H. S Ribner( Book )
1 edition published in 1972 in English and held by 5 libraries worldwide
It is shown that focussed booms that arise in turning flight can be suppressed by the simple (although not always practicable) expedient of slowing down the aircraft. The correct deceleration will eliminate the local curvature of the wave front responsible for the focussing. Specifically, the tangential deceleration resolved along the normal to the wave front is adjusted to cancel out the centripetal acceleration similarly resolved. Horizontal turns of a prescribed limiting sharpness are not of concern for this suppression TECHNIQUE: their focussed booms will be cut off from reaching the ground by atmospheric refraction. The minimum turn radius for focus cutoff is related herein in a simple fashion to the tabulated width of the sonic boom carpet for rectilinear flight, as a function of Mach number and altitude
Acoustic energy flux from shock-turbulence interaction by H. S Ribner( Book )
1 edition published in 1967 in English and held by 4 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)
Stability derivatives of triangular wings at supersonic speeds by H. S Ribner( Book )
2 editions published in 1948 in English and held by 4 libraries worldwide
The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds in NACA TN No. 1423 is extended to triangular wings having larger vertex angles and traveling at supersonic speeds. Fifteen longitudinal and lateral derivatives, including the work of others, are presented with respect to both body axes and stability axes. Results are limited to Mach numbers for which the triangle is within the Mach cone
Some conical and quasi-conical flows in linearized supersonic-wing theory by H. S Ribner( Book )
3 editions published in 1950 in English and held by 3 libraries worldwide
A number of conical and quasi-conical linearized supersonic flows have been derived. These flows may be applied in lift-cancellation techniques in the determination of wing-lift disturbances that arise at subsonic trailing edges. Some of the results are applied to damping in roll and pitch in another paper
The noise of aircraft by H. S Ribner( Book )
1 edition published in 1964 in English and held by 3 libraries worldwide
Time-dependent downwash at the tail and the pitching moment due to normal acceleration at supersonic speeds by H. S Ribner( Book )
2 editions published in 1950 in English and held by 3 libraries worldwide
The time-dependent downwash behind a wing in a supersonic stream is analyzed for the case when the angle of attack varies linearly with time. The results is applied to the calculation of the contribution of the horizontal tail to the pitching moment and lift due to normal acceleration of the airplane. The pitching moment due to normal acceleration, together with the damping in pitch, determines the damping of the short-period mode of longitudinal oscillation for an airplane
Interaction between a supersonic stream and a parallel subsonic stream bounded by fluid at rest by H. S Ribner( Book )
3 editions published in 1952 in English and held by 3 libraries worldwide
Tsien and Finston's simplified model of shock boundary-layer interaction is modified to introduce effects of the separated "dead-air" bubble, where one exists. The boundary layer is simulated by an inviscid uniform subsonic stream bounded below by fluid at rest and impinged on above by a week oblique shock in an infinite supersonic stream. Linearized analysis indicates that the simulated boundary layer approximates the expansive corner turn that would occur if the shock were incident directly on the dead-air region; there are localized distortions top and bottom
Theory of wings in slipstreams by H. S Ribner( Book )
1 edition published in 1959 in English and held by 3 libraries worldwide
A theory of the sound from jets and other flows in terms of simple sources by H. S Ribner( Book )
2 editions published in 1960 in English and held by 3 libraries worldwide
On the Effect of subsonic trailing edges on damping in roll and pitch of thin sweptback wings in a supersonic stream by H. S Ribner( Book )
3 editions published in 1950 in English and held by 3 libraries worldwide
The principal effect of subsonic trailing edges on the damping in roll and pitch of thin sweptback wings in a supersonic stream is evaluated in the form of approximate correction terms. These terms are to be added to the corresponding expressions obtained when the trailing-edge disturbances are ignored. Application is limited to plan forms and Mach numbers for which the trailing-edge disturbance does not extend beyond the leading edge and for which the area of mutual tip-trailing-edge interference is not large
An experimental investigation of turbulence-excited panel vibration and noise (boundary-layer noise) by M. Y El Baroudi( Book )
3 editions published in 1963 in English and Undetermined and held by 3 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
Aerodynamic sound from fluid dilatations : a theory of the sound from jets and other flows by H. S Ribner( Book )
1 edition published in 1962 in English and held by 2 libraries worldwide
Field of flow about a jet and effect of jets on stability of jet-propelled airplanes by H. S Ribner( Book )
2 editions published in 1946 in English and held by 2 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
 
moreShow More Titles
fewerShow Fewer Titles
Alternative Names
Ribner, Herbert S.
Ribner, Herbert S. 1913-
Languages
English (54)
Close Window

Please sign in to WorldCat 

Don't have an account? You can easily create a free account.