WorldCat Identities

Swanson, Robert Sterling

Overview
Works: 60 works in 96 publications in 1 language and 471 library holdings
Genres: History 
Roles: Author
Classifications: TP1120, 668.4
Publication Timeline
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Most widely held works about Robert Sterling Swanson
 
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Most widely held works by Robert Sterling Swanson
Plastics technology : basic materials and processes by Robert S Swanson( Book )

6 editions published between 1965 and 1968 in English and held by 327 WorldCat member libraries worldwide

Analysis of available data on the effectiveness of ailerons without exposed overhang balance by Robert S Swanson( Book )

5 editions published in 1944 in English and held by 6 WorldCat member libraries worldwide

A considerable amount of two- and three-dimensional data on the effectiveness of ailerons without exposed overhang balance has been collected and analyzed. The trends indicated by the analysis have been summarized in the form of a few approximate rules concerning the effectiveness parameter (at constant lift): Thickening and beveling the trailing edge (as measured by the trailing edge angle) will generally reduce the effectiveness about 0.3 percent per degree of bevel for ailerons sealed at the hinge axis and about 0.6 percent per degree of bevel for unsealed ailerons
Determination of the stability and control characteristics of airplanes from tests of powered models by Isidore G Recant( Book )

4 editions published in 1942 in English and held by 5 WorldCat member libraries worldwide

A technique of testing wind-tunnel powered models has been developed as a result of experience gained in the investigation of the static longitudinal and lateral stability and control characteristics of several powered models in the NACA 7- by 10-foot wind tunnel. As an important part of this technique, a minimum program of the tests considered necessary to specify satisfactorily the static stability and control characteristics for present-day airplanes has been tentatively established
Lifting -surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces by Robert S Swanson( Book )

2 editions published in 1947 in English and held by 5 WorldCat member libraries worldwide

A limited number of lifting-surface-theory solutions for wings with chordwise loadings resulting from angle of attack, parabolic-arc camber, and flap deflection are now available. These solutions were studied with the purpose of determining methods of extrapolating the results in such a way that they could be used to determine lifting-surface-theory values of the aspect-ratio corrections to the lift and hinge-moment parameters for both angle-of-attack and flap-deflection-type loading that could be used to predict the characteristics of horizontal tail surfaces from section data with sufficient accuracy for engineering purposes. Such a method was devised for horizontal tail surfaces with full-span elevators. In spite of the fact that the theory involved is rather complex, the method is simple to apply, and may be applied without any knowledge of lifting-surface-theory
Lifting-surface-theory values of the damping in roll and of the parameter used in estimating aileron stick forces by Robert S Swanson( Book )

4 editions published in 1945 in English and held by 5 WorldCat member libraries worldwide

An investigation was made by lifting-surface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagnetic-analogy method. From the results, aspect-ratio corrections for the damping in roll and aileron hinge moments for a wing in steady roll were obtained that are considerably more accurate than those given by lifting-line theory. First-order effects of the compressibility were included in the computations
Wind-tunnel tests of an NACA 23021 airfoil equipped with a slotted extensible and a plain extensible flap by Thomas A Harris( Book )

2 editions published in 1940 in English and held by 5 WorldCat member libraries worldwide

The results showed that the basic airfoil gave the lowest profile-drag coefficients over the low lift range, the airfoil with the plain extensible flap gave the lowest profile-drag coefficients over the high lift range. The airfoil with the slotted extensivle flap had the same maximum lift at a flap deflection of 25 degrees as the airfoil with the plain extensible flap had at a flap deflection of 60 degrees. The results of comparisons of the airfoil pitching-moment coefficients obtained with the two types of flap are dependent upon the basis chosen for comparison
A Lifting-surface-theory solution and tests of an elliptic tail surface of aspect ratio 3 with a 0.5-chord 0.85-span elevator by Robert S Swanson( Book )

2 editions published in 1947 in English and held by 5 WorldCat member libraries worldwide

An electromagnetic-analogy model of the vortex load, estimated from lifing-line theory with an arbitrary fairing near the elevator tip, on a thin elliptic horizontal tail surface of aspect ratio 3 with a 0.5-chord 0.85-span plain elevator was constructed and tested. The aspect-ratio corrections to the lift and hinge moments were calculated from the measured results
An electromagnetic-analogy method of solving lifting-surface-theory problems by Robert S Swanson( Book )

3 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide

A method is suggested for making lifting-surface calculations by means of magnetic measurements of an electromagnetic-analogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the induced-velocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magnetic-field string is determined by measuring, with an electronic voltmeter, the voltage induced in a small search coil by the alternating current in the wires representing the vortex sheet
Wind-tunnel development of a plug-type spoiler-slot aileron for a wing with a full-span slotted flap and a discussion of its application by Francis M Rogallo( Book )

3 editions published in 1941 in English and held by 4 WorldCat member libraries worldwide

Wind-tunnel tests were made regarding aileron to determine static rolling, yawing, and hinge moments for several angles of attack and flap deflections. Aileron is essentially a tapered plug which is fitted into slot through wing and conforms to external wing contour when in neutral position. Results indicated aileron has negligible drag in neutral position and provides satisfactory lateral control for airplanes equipped with full-span slotted flaps; it is unsatisfactory with full-span split flap. Application of aileron to pursuit type airplane is considered and resultant characteristics are estimated
Factors related to success in completing a master's degree at Stout State University, 1960-1968 by Robert S Swanson( Book )

2 editions published in 1969 in English and held by 4 WorldCat member libraries worldwide

The Graduate College at Stout State University commonly employs two criteria in deciding which applicants should be permitted to enroll for graduate degree programs: cumulative undergraduate grade-point average and experience. It was the purpose of this study to determine the effectiveness of these two criteria in predicting the likelihood of completing the master's degree program at Stout State University. To this purpose, this report: (1) presents a general description of the graduate students enrolled at ssu over the period 1960-68 in terms of undergraduate gpa, experience, classification, major field, summer and regular session enrollment, and degree status; (2) attempts to determine the relationship between ssu graduate students' success in obtaining a master's degree and their undergraduate GPA's; and (3) attempts to determine the relationship between ssu graduate students' success in obtaining a master's degree, and the number of years that elapsed between completion of their bachelor's degrees and entrance into graduate degree programs at Stout. (Af)
Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces by Robert S Swanson( Book )

2 editions published in 1948 in English and held by 3 WorldCat member libraries worldwide

A limited number of lifting-surface-theory solutions for wings with chordwise loadings resulting from angle of attack, parabolic-arc camber, and flap deflection are now available. These solutions were studied with the purpose of determining methods of extrapolating the results in such a way that they could be used to determine lifting-surface-theory values of the aspect-ratio corrections to the lift and hinge-moment parameters for both angle-of-attack and flap-deflection-type loading that could be used to predict the characteristics of horizontal tail surfaces from section data with sufficient accuracy for engineering purposes. Such a method was devised for horizontal tail surfaces with full-span elevators. In spite of the fact that the theory involved is rather complex, the method is simple to apply, and may be applied without any knowledge of lifting-surface-theory
Limitations of lifing-line theory for estimation of aileron hinge-moment characteristics by Robert S Swanson( Book )

2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

Hinge-moment parameters for several typical ailerons were calculated from section data with the aspect-ratio correction as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspect-ration correction, calculated by the method of lifting-surface theory, was applied to the slope of the curve of hinge-moment coefficient against angle of attack at small angles of attack. This so-called streamline-curvature correction brought the calculated and experimental results into satisfactory agreement
Wind-tunnel tests of a twin-engine model to determine the effect of direction of propeller rotation on the static-stability characteristics by Francis M Rogallo( Book )

2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

Tests were made in the LMAL 7- by 10-foot tunnel to determine the effect of direction of propeller rotation on the static longitudinal- and lateral-stability characteristics of the 1/10-scale model of the North American B-28 airplane
Jet-boundary corrections to the downwash behind powered models in rectangular wind tunnels with numerical values for 7- by 10-foot closed wind tunnels by Robert S Swanson( Book )

2 editions published in 1942 in English and held by 3 WorldCat member libraries worldwide

Methods are presented for determining the jet-boundary corrections to the downwash behind models in rectangular wind tunnels. The methods take into account the tunnel dimensions, the type of jet, the span loading of the model, the geometric position of the wing and of the tail in the tunnel, the displacement of the wing wake, and the effect of slipstream. A correction to the lift of the wing due to the curvature of the streamlines was determined from the downwash correction calculations and is included in the appendix. Numerical values of the downwash correction factors for 7- by 10-foot closed wind tunnels are presented in the form of graphs
Jet-boundary corrections to a yawed model in a closed rectangular wind tunnel by Robert S Swanson( Book )

3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

General formulas are derived for determining the jet-boundary corrections to the angle of attack, the drag coefficient, the downwash, the pitching-, rolling-, and yawing-moment coefficients of complete powered yawed models, and to the increments of rolling- and yawing-moment coefficients due to the ailerons on yawed models. Numerical values of the jet-boundary induced velocities and the corresponding corrections are calculated for a typical powered model yawed 20 degrees in a 7- by 10-foot closed wind tunnel. The results of the calculations are compared with the results for the unyawed model
Wind-tunnel investigation of an NACA 23021 airfoil with two sizes of balanced split flaps by Robert S Swanson( Book )

2 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide

An investigation has been made in the NACA 7- by 10-foot wind tunnel of a large-chord NACA 23021 airfoil with a 15-percent-chord and a 25-percent-chord balanced split flap of Clark Y profile, to determine the aerodynamic section characteristics of the airfoil-flap combinations as affected by the size, nose location, and deflection of the flaps. Section lift, drag, and pitching-moment characteristics are presented in the form of contours of flap nose location for given values of the lift, drag, and pitching-moment coefficients and complete aerodynamic section characteristics are presented for four representative locations of each flap. The two balanced split flaps are compared with a slotted-flap arrangement in a previous investigation
Wind-tunnel calibration and correction procedures for three-dimensional models by Robert S Swanson( Book )

3 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide

Detailed methods are presented for determining the corrections to results from wind-tunnel tests of three-dimensional models for the effects of the model-support system, the nonuniform air flow in the tunnel, and the tunnel walls or jet boundaries. The procedures for determining the corrections are illustrated by equations and the required tests are discussed. Particular attention is given to the parts of the procedures dealing with drag measurements. Two general methods that are used for determining and applying the corrections to force tests are discussed. Some discussion is also included of the correction procedures to be used for wake survey tests. The methods described in this report apply only to tests at subcritical speeds
Jet-boundary corrections for reflection-plane models in rectangular wind tunnels by Robert S Swanson( Book )

3 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

A detailed method for determining the jet-boundary corrections for reflection-plane models in rectangular wind tunnels is presented. The method includes the determination of the tunnel span load distribution and the derivation of equations for the corrections to the angle of attack, the lift and drag coefficients, and the pitching-, rolling-, yawing-, and hinge-moment coefficients. The principal effects of aerodynamic induction and of the boundary-induced curvature of the streamlines have been considered. An example is included to illustrate the method. Numerical values of the more important corrections for reflection-plane models in 7- by 10-foot closed wind tunnels is presented
Affirmative action program : the University of Wisconsin-Stout by Wisconsin( Book )

1 edition published in 1973 in English and held by 2 WorldCat member libraries worldwide

Interview by David P Barnard( Recording )

1 edition published in 1993 in English and held by 1 WorldCat member library worldwide

Description: Tape recorded interview of David Barnard by Robert Swanson in 1993 at Menomonie, Wisconsin. Barnard worked at Stout for forty-one years, beginning his career teaching graphic arts. He later taught audio-visual education, served as director of the Audio-visual Center and chair of the Media Technology Dept. He was appointed Dean of Learning Resources in 1970 and served in that capacity until his retirement in 1987. The interview includes discussion about student life at Stout in 1940; development of the audio-visual curriculum; Stout film production; the start of television at the university; development of the graduate program in Media Technology; his service as advisor to the Tower yearboook; library development; origins of Academic Computing; and comments on various Stout administrators including Verne Fryklund, William Micheels, Robert Swanson, and Clyde Bowman
 
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Languages
English (67)