Swanson, Robert Sterling
Overview
Works:  59 works in 95 publications in 1 language and 461 library holdings 

Genres:  History 
Roles:  Author 
Classifications:  TP1120, 668.4 
Publication Timeline
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Most widely held works about
Robert Sterling Swanson
 Chancellor's addresses to the faculty and staff of University of WisconsinStout by Robert S Swanson( Book )
 Making a difference : Robert S. Swanson, Chancellor( Book )
 Newspaper articles( )
 Scrapbooks by University of WisconsinStout( )
 Chancellor's commencement addresses to the graduating classes of University of WisconsinStout by Robert S Swanson( Book )
 Subject and correspondence file by University of WisconsinStout( )
 Interview by Dwight Agnew( Recording )
 Personal papers and publications by Robert S Swanson( )
 Panel discussion by Robert S Swanson( Recording )
 Speech by Robert S Swanson( Recording )
 Interview by David P Barnard( Recording )
 Interview by Herman C Arneson( Recording )
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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 328 WorldCat member libraries worldwide
6 editions published between 1965 and 1968 in English and held by 328 WorldCat member libraries worldwide
Windtunnel 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 profiledrag coefficients over the low lift range, the airfoil with the plain extensible flap gave the lowest profiledrag 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 pitchingmoment coefficients obtained with the two types of flap are dependent upon the basis chosen for comparison
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 profiledrag coefficients over the low lift range, the airfoil with the plain extensible flap gave the lowest profiledrag 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 pitchingmoment coefficients obtained with the two types of flap are dependent upon the basis chosen for comparison
A Liftingsurfacetheory solution and tests of an elliptic tail surface of aspect ratio 3 with a 0.5chord 0.85span elevator by
Robert S Swanson(
Book
)
2 editions published in 1947 in English and held by 5 WorldCat member libraries worldwide
An electromagneticanalogy model of the vortex load, estimated from lifingline theory with an arbitrary fairing near the elevator tip, on a thin elliptic horizontal tail surface of aspect ratio 3 with a 0.5chord 0.85span plain elevator was constructed and tested. The aspectratio corrections to the lift and hinge moments were calculated from the measured results
2 editions published in 1947 in English and held by 5 WorldCat member libraries worldwide
An electromagneticanalogy model of the vortex load, estimated from lifingline theory with an arbitrary fairing near the elevator tip, on a thin elliptic horizontal tail surface of aspect ratio 3 with a 0.5chord 0.85span plain elevator was constructed and tested. The aspectratio corrections to the lift and hinge moments were calculated from the measured results
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 5 WorldCat member libraries worldwide
A considerable amount of two and threedimensional 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 trailingedge 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 partialspan flaps has no consistent effect on the effectiveness. Increases in Mach number and forward movement of the transition point decrease the aileron effectiveness
5 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide
A considerable amount of two and threedimensional 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 trailingedge 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 partialspan flaps has no consistent effect on the effectiveness. Increases in Mach number and forward movement of the transition point decrease the aileron effectiveness
Lifting surfacetheory aspectratio corrections to the lift and hingemoment parameters for fullspan 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 liftingsurfacetheory solutions for wings with chordwise loadings resulting from angle of attack, parabolicarc 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 liftingsurfacetheory values of the aspectratio corrections to the lift and hingemoment parameters for both angleofattack and flapdeflectiontype 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 fullspan 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 liftingsurfacetheory
2 editions published in 1947 in English and held by 5 WorldCat member libraries worldwide
A limited number of liftingsurfacetheory solutions for wings with chordwise loadings resulting from angle of attack, parabolicarc 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 liftingsurfacetheory values of the aspectratio corrections to the lift and hingemoment parameters for both angleofattack and flapdeflectiontype 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 fullspan 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 liftingsurfacetheory
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 4 WorldCat member libraries worldwide
A technique of testing windtunnel 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 10foot 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 presentday airplanes has been tentatively established
4 editions published in 1942 in English and held by 4 WorldCat member libraries worldwide
A technique of testing windtunnel 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 10foot 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 presentday airplanes has been tentatively established
An electromagneticanalogy method of solving liftingsurfacetheory 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 liftingsurface calculations by means of magnetic measurements of an electromagneticanalogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the inducedvelocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magneticfield 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
3 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
A method is suggested for making liftingsurface calculations by means of magnetic measurements of an electromagneticanalogy model. The method is based on the perfect analogy between the strength of the magnetic field around a conductor and the strength of the inducedvelocity field around a vortex. Electric conductors are arranged to represent the vortex sheet. The magneticfield 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
Liftingsurfacetheory 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 4 WorldCat member libraries worldwide
An investigation was made by liftingsurface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagneticanalogy method. From the results, aspectratio 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 liftingline theory. Firstorder effects of the compressibility were included in the computations
4 editions published in 1945 in English and held by 4 WorldCat member libraries worldwide
An investigation was made by liftingsurface theory of a thin elliptic wing of aspect ratio 6 in a steady roll by means of the electromagneticanalogy method. From the results, aspectratio 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 liftingline theory. Firstorder effects of the compressibility were included in the computations
Windtunnel development of a plugtype spoilerslot aileron for a wing with a fullspan slotted flap and a discussion of its
application by Francis M Rogallo(
Book
)
3 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide
Windtunnel 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 fullspan slotted flaps; it is unsatisfactory with fullspan split flap. Application of aileron to pursuit type airplane is considered and resultant characteristics are estimated
3 editions published in 1941 in English and held by 3 WorldCat member libraries worldwide
Windtunnel 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 fullspan slotted flaps; it is unsatisfactory with fullspan 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, 19601968 by
Robert S Swanson(
Book
)
2 editions published in 1969 in English and held by 3 WorldCat member libraries worldwide
2 editions published in 1969 in English and held by 3 WorldCat member libraries worldwide
Liftingsurfacetheory aspectratio corrections to the lift and hingemoment parameters for fullspan 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 liftingsurfacetheory solutions for wings with chordwise loadings resulting from angle of attack, parabolicarc 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 liftingsurfacetheory values of the aspectratio corrections to the lift and hingemoment parameters for both angleofattack and flapdeflectiontype 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 fullspan 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 liftingsurfacetheory
2 editions published in 1948 in English and held by 3 WorldCat member libraries worldwide
A limited number of liftingsurfacetheory solutions for wings with chordwise loadings resulting from angle of attack, parabolicarc 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 liftingsurfacetheory values of the aspectratio corrections to the lift and hingemoment parameters for both angleofattack and flapdeflectiontype 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 fullspan 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 liftingsurfacetheory
Jetboundary 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 2 WorldCat member libraries worldwide
General formulas are derived for determining the jetboundary corrections to the angle of attack, the drag coefficient, the downwash, the pitching, rolling, and yawingmoment coefficients of complete powered yawed models, and to the increments of rolling and yawingmoment coefficients due to the ailerons on yawed models. Numerical values of the jetboundary induced velocities and the corresponding corrections are calculated for a typical powered model yawed 20 degrees in a 7 by 10foot closed wind tunnel. The results of the calculations are compared with the results for the unyawed model
3 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
General formulas are derived for determining the jetboundary corrections to the angle of attack, the drag coefficient, the downwash, the pitching, rolling, and yawingmoment coefficients of complete powered yawed models, and to the increments of rolling and yawingmoment coefficients due to the ailerons on yawed models. Numerical values of the jetboundary induced velocities and the corresponding corrections are calculated for a typical powered model yawed 20 degrees in a 7 by 10foot closed wind tunnel. The results of the calculations are compared with the results for the unyawed model
Jetboundary corrections to the downwash behind powered models in rectangular wind tunnels with numerical values for 7 by
10foot 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 jetboundary 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 10foot closed wind tunnels are presented in the form of graphs
2 editions published in 1942 in English and held by 2 WorldCat member libraries worldwide
Methods are presented for determining the jetboundary 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 10foot closed wind tunnels are presented in the form of graphs
Limitations of liftingline theory for estimation of aileron hingemoment characteristics by
Robert S Swanson(
Book
)
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
Hingemoment parameters for several typical ailerons were calculated from section data with the aspectratio correction as usually determined from liftingline theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspectration correction, calculated by the method of liftingsurface theory, was applied to the slope of the curve of hingemoment coefficient against angle of attack at small angles of attack. This socalled streamlinecurvature correction brought the calculated and experimental results into satisfactory agreement
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
Hingemoment parameters for several typical ailerons were calculated from section data with the aspectratio correction as usually determined from liftingline theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory. An additional aspectration correction, calculated by the method of liftingsurface theory, was applied to the slope of the curve of hingemoment coefficient against angle of attack at small angles of attack. This socalled streamlinecurvature correction brought the calculated and experimental results into satisfactory agreement
Jetboundary corrections for reflectionplane models in rectangular wind tunnels by
Robert S Swanson(
Book
)
3 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
A detailed method for determining the jetboundary corrections for reflectionplane 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 hingemoment coefficients. The principal effects of aerodynamic induction and of the boundaryinduced curvature of the streamlines have been considered. An example is included to illustrate the method. Numerical values of the more important corrections for reflectionplane models in 7 by 10foot closed wind tunnels is presented
3 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
A detailed method for determining the jetboundary corrections for reflectionplane 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 hingemoment coefficients. The principal effects of aerodynamic induction and of the boundaryinduced curvature of the streamlines have been considered. An example is included to illustrate the method. Numerical values of the more important corrections for reflectionplane models in 7 by 10foot closed wind tunnels is presented
Faculty and Academic Staff Handbook. University of WisconsinStout, Menomonie, Wisconsin by
Robert S Swanson(
Book
)
1 edition published in 1975 in English and held by 2 WorldCat member libraries worldwide
Procedures and regulations providing for the efficient operation of the University of Wisconsin  Stout are outlined in the 1975 edition of the faculty and academic staff handbook. Areas that are detailed include the administration of the university; faculty welfare including appointments, promotions, equal opportunity and affirmative action, tenure, dismissal, academic freedom, scholarly endeavors and research, insurance, and salaries; public information; faculty responsibilities and duties; facilities and equipment; instructional services; personal services; facultystudent committees; professional organizations; information concerning students; and the code of ethics. (Jmf)
1 edition published in 1975 in English and held by 2 WorldCat member libraries worldwide
Procedures and regulations providing for the efficient operation of the University of Wisconsin  Stout are outlined in the 1975 edition of the faculty and academic staff handbook. Areas that are detailed include the administration of the university; faculty welfare including appointments, promotions, equal opportunity and affirmative action, tenure, dismissal, academic freedom, scholarly endeavors and research, insurance, and salaries; public information; faculty responsibilities and duties; facilities and equipment; instructional services; personal services; facultystudent committees; professional organizations; information concerning students; and the code of ethics. (Jmf)
Affirmative action program : the University of WisconsinStout by
Wisconsin(
Book
)
1 edition published in 1973 in English and held by 2 WorldCat member libraries worldwide
1 edition published in 1973 in English and held by 2 WorldCat member libraries worldwide
Windtunnel 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 10foot wind tunnel of a largechord NACA 23021 airfoil with a 15percentchord and a 25percentchord balanced split flap of Clark Y profile, to determine the aerodynamic section characteristics of the airfoilflap combinations as affected by the size, nose location, and deflection of the flaps. Section lift, drag, and pitchingmoment characteristics are presented in the form of contours of flap nose location for given values of the lift, drag, and pitchingmoment coefficients and complete aerodynamic section characteristics are presented for four representative locations of each flap. The two balanced split flaps are compared with a slottedflap arrangement in a previous investigation
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 10foot wind tunnel of a largechord NACA 23021 airfoil with a 15percentchord and a 25percentchord balanced split flap of Clark Y profile, to determine the aerodynamic section characteristics of the airfoilflap combinations as affected by the size, nose location, and deflection of the flaps. Section lift, drag, and pitchingmoment characteristics are presented in the form of contours of flap nose location for given values of the lift, drag, and pitchingmoment coefficients and complete aerodynamic section characteristics are presented for four representative locations of each flap. The two balanced split flaps are compared with a slottedflap arrangement in a previous investigation
Windtunnel calibration and correction procedures for threedimensional models by
Robert S Swanson(
Book
)
3 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 windtunnel tests of threedimensional models for the effects of the modelsupport 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
3 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 windtunnel tests of threedimensional models for the effects of the modelsupport 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
Windtunnel tests of a twinengine model to determine the effect of direction of propeller rotation on the staticstability
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 10foot tunnel to determine the effect of direction of propeller rotation on the static longitudinal and lateralstability characteristics of the 1/10scale model of the North American B28 airplane
2 editions published in 1943 in English and held by 2 WorldCat member libraries worldwide
Tests were made in the LMAL 7 by 10foot tunnel to determine the effect of direction of propeller rotation on the static longitudinal and lateralstability characteristics of the 1/10scale model of the North American B28 airplane
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Related Identities
 United States National Advisory Committee for Aeronautics
 Langley Aeronautical Laboratory
 Crandall, Stewart M.
 University of WisconsinStout Oral History Program
 Priddy, E. LaVerne
 Micheels, William J. (William Jordan) 19112000
 Harris, Thomas A. Author
 NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
 Fryklund, Verne C. 18961980
 Recant, Isidore G. Author
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