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  • 1
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    Aerospace Engineering Systems and the Advanced Design Technologies Testbed Experience (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Continuous improvement of aerospace product development processes is a driving requirement across much of the aerospace community. As up to 90% of the cost of an aerospace product is committed during the first 10% of the development cycle, there is a strong emphasis on capturing, creating, and communicating better information (both requirements and performance) early in the product development process. The community has responded by pursuing the development of computer-based systems designed to enhance the decision-making capabilities of product development individuals and teams. Recently, the historical foci on sharing the geometrical representation and on configuration management are being augmented: 1) Physics-based analysis tools for filling the design space database; 2) Distributed computational resources to reduce response time and cost; 3) Web-based technologies to relieve machine-dependence; and 4) Artificial intelligence technologies to accelerate processes and reduce process variability. The Advanced Design Technologies Testbed (ADTT) activity at NASA Ames Research Center was initiated to study the strengths and weaknesses of the technologies supporting each of these trends, as well as the overall impact of the combination of these trends on a product development event. Lessons learned and recommendations for future activities are reported.
    Keywords: Engineering (General)
    Type: HPCCP/CAS Workshop Proceedings 1998; 197-204; NASA/CP-1999-208757
    Format: text
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  • 2
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    Application of digital holographic interferometry to pressure measurements of symmetric, supercritical and circulation-control airfoils in transonic flow fields (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Six airfoil interferograms were evaluated using a semiautomatic image-processor system which digitizes, segments, and extracts the fringe coordinates along a polygonal line. The resulting fringe order function was converted into density and pressure distributions and a comparison was made with pressure transducer data at the same wind tunnel test conditions. Three airfoil shapes were used in the evaluation to test the capabilities of the image processor with a variety of flows. Symmetric, supercritical, and circulation-control airfoil interferograms provided fringe patterns with shocks, separated flows, and high-pressure regions for evaluation. Regions along the polygon line with very clear fringe patterns yielded results within 1% of transducer measurements, while poorer quality regions, particularly near the leading and trailing edges, yielded results that were not as good.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-88358 , A-86402 , NAS 1.15:88358
    Format: application/pdf
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  • 3
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    Geometric analysis of wing sections (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes a new geometric analysis procedure for wing sections. This procedure is based on the normal mode analysis for continuous functions. A set of special shape functions is introduced to represent the geometry of the wing section. The generators of the NACA 4-digit airfoils were included in this set of shape functions. It is found that the supercritical wing section, Korn airfoil, could be well represented by a set of ten shape functions. Preliminary results showed that the number of parameters to define a wing section could be greatly reduced to about ten. Hence, the present research clearly advances the airfoil design technology by reducing the number of design variables.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-110346 , A-950049 , NAS 1.15:110346
    Format: application/pdf
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  • 4
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    Wake coupling to full potential rotor analysis code (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The wake information from a helicopter forward flight code is coupled with two transonic potential rotor codes. The induced velocities for the near-, mid-, and far-wake geometries are extracted from a nonlinear rigid wake of a standard performance and analysis code. These, together with the corresponding inflow angles, computation points, and azimuth angles, are then incorporated into the transonic potential codes. The coupled codes can then provide an improved prediction of rotor blade loading at transonic speeds.
    Keywords: AERODYNAMICS
    Type: NASA-TM-102805 , A-90117 , NAS 1.15:102805
    Format: application/pdf
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  • 5
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    Wing design code using three-dimensional Euler equations and optimization (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes a new wing design code which is based on the Euler equations and a constrained numerical optimization technique. The geometry modification is based on a set of fundamental modes define on the unit interval. A design example involving a high speed civil transport wing is presented to demonstrate the usefulness of the design code. It is shown that the use of an Euler solver in the direct numerical optimization procedures is affordable on the current generation of supercomputers.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3190
    Format: text
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  • 6
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    Application of digital holographic interferometry to pressure measurements of symmetric, supercritical, and circulation control airfoils in transonic flow fields (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Six airfoil interferograms were evaluated using a semiautomatic image-processor system which digitizes, segments, and extracts the fringe coordinates along a polygonal line. The resulting fringe order function was converted into density and pressure distributions and a comparison was made with pressure transducer data at the same wind tunnel test conditions. Three airfoil shapes were used in the evaluation to test the capabilities of the image processor with a variety of flows. Symmetric, supercritical, and circulation-control airfoil interferograms provided fringe patterns with shocks, separated flows, and high-pressure regions for evaluation. Regions along the polygon line with very clear fringe patterns yielded results within 1 percent of transducer measurements, while poorer quality regions, particularly near the leading and trailing edges, yielded results that were not as good.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: High speed photography, videography, and photonics IV; Aug. 19, 20, 1986; San Diego, CA; United States
    Format: text
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  • 7
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    Developments at the Advanced Design Technologies Testbed (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A report presents background and historical information, as of August 1998, on the Advanced Design Technologies Testbed (ADTT) at Ames Research Center. The ADTT is characterized as an activity initiated to facilitate improvements in aerospace design processes; provide a proving ground for product-development methods and computational software and hardware; develop bridging methods, software, and hardware that can facilitate integrated solutions to design problems; and disseminate lessons learned to the aerospace and information technology communities.
    Keywords: Man/System Technology and Life Support
    Type: ARC-14303-1 , NASA Tech Briefs, December 2003; 33
    Format: application/pdf
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  • 8
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    Aerospace Engineering Systems (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Continuous improvement of aerospace product development processes is a driving requirement across much of the aerospace community. As up to 90% of the cost of an aerospace product is committed during the first 10% of the development cycle, there is a strong emphasis on capturing, creating, and communicating better information (both requirements and performance) early in the product development process. The community has responded by pursuing the development of computer-based systems designed to enhance the decision-making capabilities of product development individuals and teams. Recently, the historical foci on sharing the geometrical representation and on configuration management are being augmented: Physics-based analysis tools for filling the design space database; Distributed computational resources to reduce response time and cost; Web-based technologies to relieve machine-dependence; and Artificial intelligence technologies to accelerate processes and reduce process variability. Activities such as the Advanced Design Technologies Testbed (ADTT) project at NASA Ames Research Center study the strengths and weaknesses of the technologies supporting each of these trends, as well as the overall impact of the combination of these trends on a product development event. Lessons learned and recommendations for future activities will be reported.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: 8th International Symposium on Computational Fluid Dynamics; Sep 05, 1999 - Sep 10, 1999; Bremen; Germany|8th International Symposium on Computational Fluid Dynamics; Aug 30, 1999; Stockholm; Sweden|8th International Symposium on Computational Fluid Dynamics; Sep 03, 1999; Aachen; Germany
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  • 9
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    Optimization of Wing-Body Configurations by the Euler Equations (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: This paper describes a new wing-body design procedure which is based on the Euler equations and a constrained numerical optimization technique. The geometry modification is based on a set of fundamental modes defined on the unit interval. A design example involving a generic wing-body model is presented to demonstrate the usefulness of the design program. It is shown that the use of an Euler solver coupled with a direct numerical optimization procedure is affordable on the current generation of supercomputers.
    Keywords: Aircraft Design, Testing and Performance
    Format: text
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  • 10
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    Measuring Airflow With Digital Holographic Interferometry (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Digital image-processing system assists in analysis of holographic interferometric images of flow about airfoil. Operating semiautomatically, identifies, counts, and labels interference fringes, then processes distances between fringes into distribution of pressure on surface of airfoil. Yields data on pressure faster than manual image-analyses techniques, and data compares favorably with those obtained by manual analysis and by probe measurements of pressure. Uses computer programs evaluating interferograms along straight or curved lines represented by polygon segments. User prompted for such inputs as reference points and fringe number. Digitizes holographic interferograms of flow and processes them into data of pressure or other properties of flow.
    Keywords: ELECTRONIC SYSTEMS
    Type: ARC-12131 , NASA Tech Briefs (ISSN 0145-319X); 13; 8; P. 34
    Format: text
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