WorldCat Identities

Johnson, Harold S.

Overview
Works: 29 works in 61 publications in 2 languages and 502 library holdings
Genres: Bibliography  Academic theses 
Roles: Author, Compiler
Publication Timeline
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Most widely held works by Harold S Johnson
Self-determination within the community of nations by Harold S Johnson( Book )

13 editions published between 1962 and 1967 in English and Dutch and held by 260 WorldCat member libraries worldwide

International organization; a classified bibliography by Harold S Johnson( Book )

3 editions published in 1969 in English and held by 140 WorldCat member libraries worldwide

SCOTT (Copy 1): From the John Holmes Library Collection
Wind-tunnel investigation at low speed of lateral control characteristics of an untapered 45° sweptback semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain ailerons by Harold S Johnson( )

3 editions published between 1950 and 1951 in English and held by 22 WorldCat member libraries worldwide

A wind-tunnel investigation at low speed was made to determine the lateral control characteristics of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain unsealed ailerons. Variations of the lateral-control data with aileron span and spanwise location were determined through a large aileron-deflection range for various angles of attack up to about the angle of maximum lift
The plebiscite as an international means for self-determination by Harold S Johnson( Book )

4 editions published between 1963 and 1966 in English and held by 7 WorldCat member libraries worldwide

Wind-tunnel investigation at low speed of the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons by Harold S Johnson( Book )

4 editions published in 1950 in English and held by 6 WorldCat member libraries worldwide

A wind-tunnel investigation at low speed was made to determine the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons having various spans and spanwise locations. Variations of the lateral-control data with aileron span and spanwise location were determined through a large aileron-deflection range for various angles of attack up to about the angle of maximum lift
Wind-tunnel investigation at low speed of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain flaps by Harold S Johnson( Book )

4 editions published in 1950 in English and held by 6 WorldCat member libraries worldwide

This report contains the results and analysis of force and moment data at low speed to determine the aerodynamic characteristics of an unswept untapered semispan wing of NACA 64A010 section and aspect ratio 3.13 equipped with 25-percent-chord unsealed plain flaps having various spans and spanwise locations. Variations of the wing aerodynamic data with flap span and spanwise location were determined through a large angle-of-attack range
Wind-tunnel investigation of effects of tail length on the longitudinal and lateral stability characteristics of a single-propeller airplane model by Harold S Johnson( Book )

2 editions published in 1948 in English and held by 5 WorldCat member libraries worldwide

This report contains results and analysis of a wind-tunnel investigation at low-speed conducted to determine the effects of tail length and horizontal-tail volune on the longitudinal and lateral stability of a powered model of a single-propeller low-wing airplane with flaps retracted and deflected
Effects of trailing-edge modifications on pitching moment characteristics of airfoils by Paul E Purser( Book )

2 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide

The available data on the effects of trailing-edge modifications on the pitching-moment characteristics of airfoils have been collected and briefly analyzed. With the control-surface gap sealed, the location of the airfoil aerodynamic center moved forward as the included angle between the upper and lower surfaces of the airfoil at the trailing edge was increased and as the airfoil thickness at 0.9 chord was increased. The variation of pitching-moment coefficient with control-surface deflection, at constant lift coefficient with gap sealed, decreased as the trailing-edge angle was increased by the effects of the airfoil thickness near the trailing edge could not be determined because of insufficient data
Wind-tunnel investigation at low speed of a 45 degree sweptback untapered semispan wing of apsect ratio 1.59 equipped with various 25-percent-chord plain flaps by Harold S Johnson( Book )

1 edition published in 1950 in English and held by 3 WorldCat member libraries worldwide

A wind-tunnel investigation at low speed was made to determine the aerodynamic characteristics of a 45 degree sweptback untapered semispan wing of NACA 64A010 airfoil section with aspect ratio 1.59 equipped with 25-percent-chord unsealed plain flaps having various spans and spanwise locations. Variations of lift, drag, pitching-moment, and flap hinge-moment data with flap span and spanwise location were determined through a large angle-of-attack range
International organization : a classified bibliography by Harold S Johnson( Book )

1 edition published in 1969 in English and held by 2 WorldCat member libraries worldwide

Wind-Tunnel Investigation at Low Speed of a 45 deg Sweptback Untapered Semispan Wing of Aspect Ratio 1.59 Equipped With Various 25-Percent-Chord Plain Flaps( Book )

2 editions published in 1950 in English and held by 2 WorldCat member libraries worldwide

A wind-tunnel investigation was made at low speed to determine the aerodynamic characteristics of a 45 deg sweptback untapered semispan wing of NACA 64A010 airfoil section normal to the leading edge and aspect ratio of 1.59 equipped with 25-percent-chord plain unsealed flaps having various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the various flaps deflected up to 60 deg. A comparison is made, with data obtained on the present wing at 0 deg of sweep with an aspect ratio of 3.13. In general, changes in angle of attack, flap deflection, flap span, and spanwise location produced trends in lift, drag, pitching moment, and flap hinge moment that were similar to but of different magnitudes from those for unswept wings. Existing empirical and theoretical methods for predicting the lift effectiveness of flaps of various spans gave very good agreement with the experimental results. Because of the increase in the drag coefficients and the associated decrease in the lift-drag ratio with increasing flap deflection, an advantage may be gained by limiting the flap deflection to moderate angles (about 30 deg), even though the lift coefficients increase slightly with further increases in flap deflection. Flap deflections greater than 30 deg may be desirable, however, when steeper glide-path angles are required
International Organization : a classified bibliography by Harold S Johnson( Book )

1 edition published in 1969 in Undetermined and held by 2 WorldCat member libraries worldwide

The nitric oxide-fluorine dilute diffusion flame( Book )

1 edition published in 1960 in English and held by 1 WorldCat member library worldwide

Wind-tunnel investigation at low speed of a 45° sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain flaps by Harold S Johnson( Book )

1 edition published in 1950 in English and held by 1 WorldCat member library worldwide

Wind-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle by Harold S Johnson( Book )

1 edition published in 1949 in English and held by 1 WorldCat member library worldwide

An investigation was performed to determine the effects of number of wings on the aileron rolling effectiveness of an RM-5 test vehicle using the free-rolling wind-tunnel testing technique through a speed range to a Mach number of 0.9. Since free-flight models must have three or more wings for stability, the investigation was conducted to determine the validity of applying multiwing test results to conventional airplane configurations. The test-vehicle wings had neither taper nor sweepback and were equipped with full-span 20-percent-chord sealed and faired ailerons
The production of potassium chloride and iodine from sea weed by G. Vernon Green( )

1 edition published in 1911 in English and held by 1 WorldCat member library worldwide

 
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Alternative Names
Johnson, Harold

Johnson, Harold S.

Languages
English (49)

Dutch (1)