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
 Interview by Dwight Agnew Dwight Agnew( Recording )
 Scrapbooks by University of WisconsinStoutUniversity of WisconsinStout( )
 Panel discussion by Robert S Swanson Robert S Swanson( Recording )
 Chancellor's addresses to the faculty and staff of University of WisconsinStout by Robert S Swanson Robert S Swanson( Book )
 Interview by Herman C Arneson Herman C Arneson( Recording )
 Personal papers and publications by Robert S Swanson Robert S Swanson( )
 Speech by Robert S Swanson Robert S Swanson( Recording )
 Newspaper articles ( )
 Chancellor's commencement addresses to the graduating classes of University of WisconsinStout by Robert S Swanson Robert S Swanson( Book )
 Interview by David P Barnard David P Barnard( Recording )
 Subject and correspondence file by University of WisconsinStoutUniversity of WisconsinStout( )
 Making a difference : Robert S. Swanson, Chancellor ( Book )
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Most widely held works by
Robert S Swanson
Liftingsurfacetheory 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 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 compressibility were included in the computations. The results obtained by liftingsurface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by liftingline theory and 5 percent less than that given by liftingline theory with the edgevelocity correction derived by Robert T. Jones applied. The results are extended to wings of other aspect ratios
4 editions published in 1945 in English and held by 12 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 compressibility were included in the computations. The results obtained by liftingsurface theory indicate that the damping in roll for a wing of aspect ratio 6 is 13 percent less than that given by liftingline theory and 5 percent less than that given by liftingline theory with the edgevelocity 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 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
4 editions published in 1944 in English and held by 12 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
An electromagneticanalogy method of solving liftingsurfacetheory 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 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 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 liftingsurface problems may be obtained by placing the conductors representing the trailing vortices along the fluid lines (Helmholtz condition). A potentialflow solution for the distortion and rolling up of the trailingvortex sheet may be obtained. By use of the PrandtlGlauert rule, the liftingsurface theory may be adapted to include firstorder compressibility effects
3 editions published in 1945 in English and held by 12 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 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 liftingsurface problems may be obtained by placing the conductors representing the trailing vortices along the fluid lines (Helmholtz condition). A potentialflow solution for the distortion and rolling up of the trailingvortex sheet may be obtained. By use of the PrandtlGlauert rule, the liftingsurface theory may be adapted to include firstorder compressibility effects
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 4 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 4 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
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 4 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 4 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
)
3 editions published in 1942 in English and held by 3 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
3 editions published in 1942 in English and held by 3 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
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
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, 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
Windtunnel 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 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
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 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
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
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
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
Limitations of lifingline 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
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
)
2 editions published in 1941 in English and held by 2 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
2 editions published in 1941 in English and held by 2 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
JetBoundary Corrections for ReflectionPlane Models in Rectangular Wind Tunnels
(
)
1 edition published in 1943 in English and held by 2 WorldCat member libraries worldwide
1 edition published in 1943 in English and held by 2 WorldCat member libraries worldwide
Jetboundary 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 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
2 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
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
)
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 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
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 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
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 fortyone years, beginning his career teaching graphic arts. He later taught audiovisual education, served as director of the Audiovisual 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 audiovisual 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
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 fortyone years, beginning his career teaching graphic arts. He later taught audiovisual education, served as director of the Audiovisual 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 audiovisual 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, universitywide publications, media relations, and special projects for the chancellor. Buelow received a Bachelor of Science degree from UWMilwaukee 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
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, universitywide publications, media relations, and special projects for the chancellor. Buelow received a Bachelor of Science degree from UWMilwaukee 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
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Related Identities
 United States National Advisory Committee for Aeronautics
 Langley Aeronautical Laboratory
 Crandall, Stewart M.
 University of WisconsinStout
 University of WisconsinStout Oral History Program
 Priddy, E. LaVerne
 University of WisconsinStout Graduate College
 NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
 Micheels, William Jordan 1911
 University of WisconsinStout Chancellor
Associated Subjects
Academic achievement AerodynamicsResearch Aerofoils African AmericansEmployment Ailerons Air flow AirplanesControl surfaces AirplanesModelsTesting AirplanesTail surfaces AirplanesWings Aspect ratio (Aerofoils) Boundary layer Charts, diagrams, etc Compressibility Damping (Mechanics) Discrimination in employment Downwash (Aerodynamics) Drag (Aerodynamics) Educational broadcasting EducationCurricula Electromechanical analogies Elevators (Airplanes) Flaps (Airplanes) Graduate students Hinge moments (Aerodynamics) Lift (Aerodynamics) Magnetic fields Management Mathematics MinoritiesEmployment Multicultural education Pitching (Aerodynamics) Plastics Propellers, Aerial Rolling (Aerodynamics) Split flaps (Airplanes) Spoilers (Airplanes) Stability of airplanes Stout, James Huff, Students Technical educationCurricula Universities and collegesFaculty University of WisconsinStout University of WisconsinStout.Teleproduction Center Vortexmotion Wind tunnel models Wind tunnel testing Wisconsin WisconsinMenomonie WomenEmployment
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