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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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    NASA TECHNICAL REPORTS
  • 2
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    Flow Field Characterization of an Angled Supersonic Jet Near a Bluff Body (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experiment was performed to acquire data from a hot supersonic jet in cross flow for the purpose of validating computational fluid dynamics (CFD) turbulence modeling relevant to the Orion Launch Abort System. Hot jet conditions were at the highest temperature and pressure that could be acquired in the test facility. The nozzle pressure ratio was 28.5, and the nozzle temperature ratio was 3. These conditions are different from those of the flight vehicle, but sufficiently high to model the observed turbulence features. Stereo Particle Image Velocimetry (SPIV) data and capsule pressure data are presented. Features of the flow field are presented and discussed
    Keywords: Aerodynamics
    Type: NASA/TM-2011-216958 , AIAA Paper 2010-4829 , E-17563 , 28th AIAA Applied Aerodynamics Conference; Jun 28, 2010 - Jul 01, 2010; Chicago, IL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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