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Dansberry, Bryan E.

Publications and source records attributed to Dansberry, Bryan E..

15 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS2018

Updated Benefits for Humanity from the International Space Station

Final document is attached. In 2018, the International Space Station (ISS) [Figure 1] partnership completed a revision for the third edition of the International Space Station Benefits for Humanity, a compilation of case studies of benefits being realized from ISS activities in the areas of human health, Earth observations and disaster response, innovative technology, global education, and economic development of space. The revision included new assessments of economic value and scientific value with more detail than the second edition. The third edition contains updated statistics on the impacts of the benefits as well as new benefits that have developed since the previous publication. This presentation will summarize the updates on behalf of the ISS Program Science Forum, which consists of senior science representatives across the ISS international partnership. An independent consultant determined the economic valuation (EV) of ISS research benefits case studies and the third edition contains the results. The process involved a preliminary assessment of economic, social, and innovation factors. A more detailed assessment followed, which included factors such as addressable market, market penetration, revenue generation, ability to leverage across other applications or customer groups, quality of life improvements, health benefits, environmental benefits, cultural and community cohesion, inspiration, new knowledge, novel approaches, creation of a unique market niche, and research leadership. Because of the unique microgravity environment of the ISS laboratory, the multidisciplinary and international nature of the research, and the significance of the investment in its development, analyzing ISS scientific impacts is an exceptional challenge. As a result, the ISS partnership determined the scientific valuation (SV) of ISS research using a combination of citation analyses, bibliometrics, and narratives of important ISS utilization results. Approximately 2,100 ISS results publications comprised of scientific journal articles, conference proceedings, and gray literature, representing over 5,000 authors and co-authors on Earth were used in this evaluation to enable the communication of impacts of ISS research on various science and technology fields across many countries. The publication also updates and expands the previously described benefits of research results in the areas of space commerce, technology development, human health, environmental change and disaster response, and education activities. Distinct benefits return to Earth from the only orbiting multidisciplinary laboratory of its kind. The ISS is a stepping-stone for future space exploration while also providing findings that develop low Earth orbit as a place for sustained human activity and improve life on our planet.

research↗
NASA NTRS2018

Updated Benefits for Humanity, Third Edition (B4H3), from the International Space Station (ISS)

In 2018, the International Space Station (ISS) [Figure 1] partnership completed a revision for the third edition of the International Space Station Benefits for Humanity, a compilation of case studies of benefits being realized from ISS activities in the areas of human health, Earth observations and disaster response, innovative technology, global education, and economic development of space. The revision included new assessments of economic value and scientific value with more detail than the second edition. The third edition contains updated statistics on the impacts of the benefits as well as new benefits that have developed since the previous publication. This presentation will summarize the updates on behalf of the ISS Program Science Forum, which consists of senior science representatives across the ISS international partnership. An independent consultant determined the economic valuation (EV) of ISS research benefits case studies and the third edition contains the results. The process involved a preliminary assessment of economic, social, and innovation factors. A more detailed assessment followed, which included factors such as addressable market, market penetration, revenue generation, ability to leverage across other applications or customer groups, quality of life improvements, health benefits, environmental benefits, cultural and community cohesion, inspiration, new knowledge, novel approaches, creation of a unique market niche, and research leadership. Because of the unique microgravity environment of the ISS laboratory, the multidisciplinary and international nature of the research, and the significance of the investment in its development, analyzing ISS scientific impacts is an exceptional challenge. As a result, the ISS partnership determined the scientific valuation (SV) of ISS research using a combination of citation analyses, bibliometrics, and narratives of important ISS utilization results. Approximately 2,100 ISS results publications comprised of scientific journal articles, conference proceedings, and gray literature, representing over 5,000 authors and co-authors on Earth were used in this evaluation to enable the communication of impacts of ISS research on various science and technology fields across many countries. The publication also updates and expands the previously described benefits of research results in the areas of space commerce, technology development, human health, environmental change and disaster response, and education activities. Distinct benefits return to Earth from the only orbiting multidisciplinary laboratory of its kind. The ISS is a stepping-stone for future space exploration while also providing findings that develop low Earth orbit as a place for sustained human activity and improve life on our planet.

ISS↗
NASA NTRS1993

Physical properties of the benchmark models program supercritical wing

The goal of the Benchmark Models Program is to provide data useful in the development and evaluation of aeroelastic computational fluid dynamics (CFD) codes. To that end, a series of three similar wing models are being flutter tested in the Langley Transonic Dynamics Tunnel. These models are designed to simultaneously acquire model response data and unsteady surface pressure data during wing flutter conditions. The supercritical wing is the second model of this series. It is a rigid semispan model with a rectangular planform and a NASA SC(2)-0414 supercritical airfoil shape. The supercritical wing model was flutter tested on a flexible mount, called the Pitch and Plunge Apparatus, that provides a well-defined, two-degree-of-freedom dynamic system. The supercritical wing model and associated flutter test apparatus is described and experimentally determined wind-off structural dynamic characteristics of the combined rigid model and flexible mount system are included.

Dansberry, Bryan E.↗
NASA NTRS1993

Experimental unsteady pressures at flutter on the Supercritical Wing Benchmark Model

This paper describes selected results from the flutter testing of the Supercritical Wing (SW) model. This model is a rigid semispan wing having a rectangular planform and a supercritical airfoil shape. The model was flutter tested in the Langley Transonic Dynamics Tunnel (TDT) as part of the Benchmark Models Program, a multi-year wind tunnel activity currently being conducted by the Structural Dynamics Division of NASA Langley Research Center. The primary objective of this program is to assist in the development and evaluation of aeroelastic computational fluid dynamics codes. The SW is the second of a series of three similar models which are designed to be flutter tested in the TDT on a flexible mount known as the Pitch and Plunge Apparatus. Data sets acquired with these models, including simultaneous unsteady surface pressures and model response data, are meant to be used for correlation with analytical codes. Presented in this report are experimental flutter boundaries and corresponding steady and unsteady pressure distribution data acquired over two model chords located at the 60 and 95 percent span stations.

Dansberry, Bryan E.↗
NASA NTRS1992

Pressure measurements on a rectangular wing with a NACA0012 airfoil during conventional flutter

The Structural Dynamics Division at NASA LaRC has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of the program is to acquire measured dynamic instability and corresponding pressure data that will be useful for developing and evaluating aeroelastic type CFD codes currently in use or under development. The program is a multi-year activity that will involve testing of several different models to investigate various aeroelastic phenomena. The first model consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree-of-freedom mount system. Two wind-tunnel tests were conducted with the first model. Several dynamic instability boundaries were investigated such as a conventional flutter boundary, a transonic plunge instability region near Mach = 0.90, and stall flutter. In addition, wing surface unsteady pressure data were acquired along two model chords located at the 60 to 95-percent span stations during these instabilities. At this time, only the pressure data for the conventional flutter boundary is presented. The conventional flutter boundary and the wing surface unsteady pressure measurements obtained at the conventional flutter boundary test conditions in pressure coefficient form are presented. Wing surface steady pressure measurements obtained with the model mount system rigidized are also presented. These steady pressure data were acquired at essentially the same dynamic pressure at which conventional flutter had been encountered with the mount system flexible.

Rivera, Jose A., Jr.↗
NASA NTRS1992

NACA0012 benchmark model experimental flutter results with unsteady pressure distributions

The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of this program is to acquire measured dynamic instability and corresponding pressure data that will be useful for developing and evaluating aeroelastic type computational fluid dynamics codes currently in use or under development. The program is a multi-year activity that will involve testing of several different models to investigate various aeroelastic phenomena. This paper describes results obtained from a second wind tunnel test of the first model in the Benchmark Models Program. This first model consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree of freedom mount system. Experimental flutter boundaries and corresponding unsteady pressure distribution data acquired over two model chords located at the 60 and 95 percent span stations are presented.

Rivera, Jose A., Jr.↗
NASA NTRS1992

The benchmark aeroelastic models program: Description and highlights of initial results

An experimental effort was implemented in aeroelasticity called the Benchmark Models Program. The primary purpose of this program is to provide the necessary data to evaluate computational fluid dynamic codes for aeroelastic analysis. It also focuses on increasing the understanding of the physics of unsteady flows and providing data for empirical design. An overview is given of this program and some results obtained in the initial tests are highlighted. The tests that were completed include measurement of unsteady pressures during flutter of a rigid wing with an NACA 0012 airfoil section and dynamic response measurements of a flexible rectangular wing with a thick circular arc airfoil undergoing shock boundary layer oscillations.

Bennett, Robert M.↗
NASA NTRS1992

NACA 0012 benchmark model experimental flutter results with unsteady pressure distributions

The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of the program is to acquire measured dynamic instability and corresponding pressure data that will be useful for developing and evaluating aeroelastic type CFD codes currently in use or under development. The program is a multi-year activity that will involve testing of several different models to investigate various aeroelastic phenomena. This paper describes results obtained from a second wind tunnel test of the first model in the Benchmark Models Program. This first model consisted of a rigid semispan wing having a rectangular planform and a NACA 0012 airfoil shape which was mounted on a flexible two degree-of-freedom mount system. Experimental flutter boundaries and corresponding unsteady pressure distribution data acquired over two model chords located at the 60 and 95 percent span stations are presented.

Rivera, Jose A., Jr.↗
NASA NTRS1992

Dynamic characteristics of a Benchmark models program supercritical wing

The dynamic characteristics of the Benchmark Supercritical Wing are presented. The Benchmark Supercritical Wing is a rigid semi-span model with a rectangular planform and a supercritical airfoil shape. This model will be tested on a flexible mount system that provides a well defined, two-degree-of-freedom dynamic system. This paper defines the dynamic characteristics of the model/mount system as determined in a preliminary ground vibration test. A general description of the model, flexible mount system, and instrumentation are included as well as a summary of the data set which the testing of this model is intended to produce.

Dansberry, Bryan E.↗
NASA NTRS1991

The benchmark aeroelastic models program: Description and highlights of initial results

An experimental effort was implemented in aeroelasticity called the Benchmark Models Program. The primary purpose of this program is to provide the necessary data to evaluate computational fluid dynamic codes for aeroelastic analysis. It also focuses on increasing the understanding of the physics of unsteady flows and providing data for empirical design. An overview is given of this program and some results obtained in the initial tests are highlighted. The tests that were completed include measurement of unsteady pressures during flutter of rigid wing with a NACA 0012 airfoil section and dynamic response measurements of a flexible rectangular wing with a thick circular arc airfoil undergoing shock boundary layer oscillations.

Bennett, Robert M.↗
NASA NTRS1991

Experimental flutter boundaries with unsteady pressure distributions for the NACA 0012 Benchmark Model

The Structural Dynamics Div. at NASA-Langley has started a wind tunnel activity referred to as the Benchmark Models Program. The objective is to acquire test data that will be useful for developing and evaluating aeroelastic type Computational Fluid Dynamics codes currently in use or under development. The progress is described which was achieved in testing the first model in the Benchmark Models Program. Experimental flutter boundaries are presented for a rigid semispan model (NACA 0012 airfoil section) mounted on a flexible mount system. Also, steady and unsteady pressure measurements taken at the flutter condition are presented. The pressure data were acquired over the entire model chord located at the 60 pct. span station.

Rivera, Jose A., Jr.↗
NASA NTRS1991

Transonic shock-induced dynamics of a flexible wing with a thick circular-arc airfoil

Transonic shock boundary layer oscillations occur on rigid models over a small range of Mach numbers on thick circular-arc airfoils. Extensive tests and analyses of this phenomena have been made in the past but essentially all of them were for rigid models. A simple flexible wing model with an 18 pct. circular arc airfoil was constructed and tested in the Langley Transonic Dynamics Tunnel to study the dynamic characteristics that a wing might have under these circumstances. In the region of shock boundary layer oscillations, buffeting of the first bending mode was obtained. This mode was well separated in frequency from the shock boundary layer oscillations. A limit cycle oscillation was also measured in a third bending like mode, involving wind vertical bending and splitter plate motion, which was in the frequency range of the shock boundary layer oscillations. Several model configurations were tested, and a few potential fixes were investigated.

Bennett, Robert M.↗
NASA NTRS1991

Experimental flutter boundaries with unsteady pressure distributions for the NACA 0012 Benchmark Model

The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of the program is to acquire test data that will be useful for developing and evaluating aeroelastic type CFD codes currently in use of under development. This paper describes the progress achieved in testing the first model in the Benchmark Models Program. Experimental flutter boundaries are presented for a rigid semispan model (NACA 0012 airfoil section) mounted on a flexible mount system. Also, steady and unsteady pressure measurements taken at the flutter condition are presented. The pressure data were acquired over the entire model chord located at the 60 percent span station.

Rivera, Jose A.↗
NASA NTRS1990

An experimental study of tip shape effects on the flutter of aft-swept, flat-plate wings

The effects of tip chord orientation on wing flutter are investigated experimentally using six cantilever-mounted, flat-plate wing models. Experimentally determined flutter characteristics of the six models are presented covering both the subsonic and transonic Mach number ranges. While all models have a 60 degree leading edge sweep, a 40.97 degree trailing edge sweep, and a root chord of 34.75 inches, they are subdivided into two series characterized by a higher aspect ratio and a lower aspect ratio. Each series is made up of three models with tip chord orientations which are parallel to the free-stream flow, perpendicular to the model mid-chord line, and perpendicular to the free-stream flow. Although planform characteristics within each series of models are held constant, structural characteristics such as mode shapes and natural frequencies are allowed to vary.

Dansberry, Bryan E.↗