WorldCat Identities

Swanson, Robert S.

Overview
Works: 64 works in 87 publications in 1 language and 119 library holdings
Genres: History 
Roles: Author
Classifications: TP1120, 668.4
Publication Timeline
.
Most widely held works about Robert S Swanson
 
moreShow More Titles
fewerShow Fewer Titles
Most widely held works by Robert S Swanson
Lifting-surface-theory values of the damping in roll and of the parameter used in estimating aileron stick forces by Robert S Swanson( )
4 editions published in 1945 in English and held by 12 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 compressibility were included in the computations. The results obtained by lifting-surface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by lifting-line theory and 5 percent less than that given by lifting-line theory with the edge-velocity correction derived by Robert T. Jones applied. The results are extended to wings of other aspect ratios
Analysis of available data on the effectiveness of ailerons without exposed overhang balance by Robert S Swanson( )
4 editions published in 1944 in English and held by 12 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 [Pyramid symbol[alpha]/[Pyramid symbol[delta] (at constant lift): Thickening and beveling the trailing edge (as measured by the trailing-edge angle Ø) 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. A 0.005c gap at the hinge axis usually reduces the effectiveness approximately 17 percent for flap chord ratios of 0.2. This percentage increases as the flap chord ratio is reduced. The effectiveness is about 14 percent lower at aileron deflections of 20° than at aileron deflections of 10°. At large angles of attack (a = 10°) and for chord ratios of about 0.2, positively deflected ailerons are approximately 20 percent less effective than negatively deflected ailerons. The deflection of partial-span flaps has no consistent effect on the effectiveness. Increases in Mach number and forward movement of the transition point decrease the aileron effectiveness
An electromagnetic-analogy method of solving lifting-surface-theory problems by Robert S Swanson( )
3 editions published in 1945 in English and held by 12 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 strength 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. Solutions of nonlinear lifting-surface problems may be obtained by placing the conductors representing the trailing vortices along the fluid lines (Helmholtz condition). A potential-flow solution for the distortion and rolling up of the trailing-vortex sheet may be obtained. By use of the Prandtl-Glauert rule, the lifting-surface theory may be adapted to include first-order compressibility effects
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 4 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
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 4 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
Determination of the stability and control characteristics of airplanes from tests of powered models by Isidore G Recant( Book )
3 editions published in 1942 in English and held by 3 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
Plastics technology; basic materials and processes by Robert S Swanson( Book )
2 editions published between 1965 and 1968 in English and held by 3 WorldCat member libraries worldwide
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 3 WorldCat member libraries worldwide
Wind-tunnel tests of an NACA 23021 airfoil equipped with a slotted extensible and a plain extensible flap by Thomas A Harris( Book )
1 edition published in 1940 in English and held by 3 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
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
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 2 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
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 2 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
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 2 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 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 )
2 editions published in 1941 in English and held by 2 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
Jet-Boundary Corrections for Reflection-Plane Models in Rectangular Wind Tunnels ( )
1 edition published in 1943 in English and held by 2 WorldCat member libraries worldwide
Jet-boundary corrections to a yawed model in a closed rectangular wind tunnel by Robert S Swanson( Book )
2 editions published in 1943 in English and held by 2 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 2 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 )
2 editions published in 1944 in English and held by 2 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
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
Interview by Charles L Buelow( Recording )
1 edition published in 1992 in English and held by 1 WorldCat member library worldwide
Description: Tape recorded interview conducted by Robert Swanson with Charles Buelow on January 22, 1992. Chuck Buelow has served at Stout since 1968. During that time he provided leadership during periods of the most dramatic growth of the university in terms of student population, facilities, and staff. Buelow was instrumental in developing what is now the Office of University Relations. The office oversees legislative relations, community relations, business relations, university-wide publications, media relations, and special projects for the chancellor. Buelow received a Bachelor of Science degree from UW-Milwaukee and served as a reporter for the Milwaukee Journal for seven years before joining Stout. He retired from University Relations in 1992, but returned in 1993 on special assignment as a special assistant to the chancellor
 
moreShow More Titles
fewerShow Fewer Titles
Audience Level
0
Audience Level
1
  Kids General Special  
Audience level: 0.62 (from 0.00 for Wind-tunne ... to 1.00 for Jet-Bounda ...)
Languages
English (54)