Experiments are described in which the amplitudes of heave force, pressure at selected girthwise locations, and radiating waves, as well as the phase angles of force and pressure were measured for several heaving cylindrical bodies. These results are compared with theoretical values computed according to Porter's work. Excellent agreement is found between theoretical and measured amplitudes of force and pressure. The agreement for predicted and measured wave heights and for phase angles is...

Topics: DTIC Archive, Paulling, J R, CALIFORNIA UNIV BERKELEY INST OF ENGINEERING RESEARCH, *CYLINDRICAL...

A recent problem for which a solution was requested was that of the bending stresses in a thick-walled tube under internal pressure, restrained by heavy integral flanges at its ends and closed by end plates. The arrangement of bolts and the end-plate configuration were such that the flanges could rotate without restraint from the end plates. Although the radius-thickness ratio of the tube was so small that shell theory was almost certainly invalid, it was felt that, in the absence of a more...

Topics: DTIC Archive, SEIDE,PAUL, TRW SPACE TECHNOLOGY LABS LOS ANGELES CA LOS ANGELES United States,...

The frequency (or phase velocity) of axially symmetric free vibrations in an elastic, isotropic circular cylinder of medium thickness is studied on the basis of the three-dimensional linear theory of elasticity and also on the basis of several different shell theories.

Topics: DTIC Archive, Herrmann, G, COLUMBIA UNIV NEW YORK NEW YORK, CYLINDRICAL BODIES, VIBRATION

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

The purpose of this workshop was to review the state of knowledge of high Reynolds number (incompressible) rigid cylinder flows, to identify problem areas, and recommend research for understanding these flow conditions. The recommendations are being incorporated into the design of a comprehensive experiment that is scheduled for Spring of 1982 in the NASA Ames Research Center 12-foot pressurized wind tunnel.

Topics: DTIC Archive, Shih,W C L, PHYSICAL RESEARCH INC PALOS VERDES ESTATES CA, *CYLINDRICAL BODIES,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE, *AMMUNITION CASES,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An analytical formula for determining the direction of motion for an explosively driven metal liner under unsteady conditions is presented. This direction is defined by the angle delta between the velocity vector of the liner element and the perpendicular to the initial liner surface. A formula for determining the angle delta was first proposed by G.I. Taylor as sin delta = V/ 2U, where V is the final liner element velocity and U is the velocity by which the detonation wave front sweeps past...

Topics: DTIC Archive, Chou, Pei Chi, DYNA EAST CORP PHILADELPHIA PA, *EXPLOSIONS, *LININGS, *COLLAPSE,...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

An experimental investigation was conducted into four areas of the solid fuel ramjet combustion process: (1) the effects of near-wall turbulent mixing and equivalence ratio on combustion efficiency, (2) the effects of bypass air on combustion efficiency, (3) the combustion process in a cylindrically perforated fuel grain with a twin side-dump/dome configuration, and (4) the comparison of experimental radial temperature profiles to computer generated radial profiles. Polymethylmethacrylate fuel...

Topics: DTIC Archive, Goodwin,William Vernon, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *COMBUSTION, *SOLID...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

The angular distribution of incident particles is obtained for attracted and repelled particles incident on a charged cylindrical spacecraft. The angular distributions are important when backscattering and secondary emission are significant processes. Results are given for planes and spheres as well. (Author)

Topics: DTIC Archive, Besse,Arthur L, AIR FORCE GEOPHYSICS LAB HANSCOM AFB MA, *PARTICLE SPECTRA, *SPACE...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...

This technical report describes the technology and instrumentation developed for the measurement of vector electric and magnetic fields with cylindrical configurations, when the configurations are illuminated by a plane electromagnetic wave in the frequency range of 225 to 400 MHz. A set of such contour maps are presented for a missile nosecone and a right circular cylinder illuminated by a 300 MHz planewave. (Author)

Topics: DTIC Archive, Goulette,Richard R, BELL NORTHERN RESEARCH LTD OTTAWA (ONTARIO), *REENTRY VEHICLES,...