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  • 1
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    Sensitivity Derivatives for Advanced CFD Algorithm and Viscous Modeling Parameters via Automatic Differentiation (1996)
    Elsevier
    Details
    Publication Date: 1996-05-01
    Print ISSN: 0021-9991
    Electronic ISSN: 1090-2716
    Topics: Computer Science , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Wall interference assessment/correction for transonic airfoil data (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 774-780
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Nonlinear transonic Wall-Interference Assessment/Correction (WIAC) procedures and application to cast-10 airfoil results from the NASA 0.3-m TCT 8- by 24-inch Slotted Wall Test Section (SWTS) (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: From the time that wind tunnel wall interference was recognized to be significant, researchers have been developing methods to alleviate or account for it. Despite the best effort so far, it appears that no method is available which completely eliminates the effects due to the wind tunnel walls. This report discusses procedures developed for slotted wall and adaptive wall test sections of the Langley 0.3-m Transonic Cryogenic Tunnel (TCT) to assess and correct for the residual interference by methods consistent with the transonic nature of the tests.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: CAST-10-2(DOA 2 Airfoil Studies Workshop Results; p 9-35
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Finite-volume scheme for transonic potential flow about airfoils and bodies in an arbitrarily shaped channel (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A conservative finite-volume difference scheme is developed for the potential equation to solve transonic flow about airfoils and bodies in an arbitrarily shaped channel. The scheme employs a mesh which is a nearly conformal O mesh about the airfoil and nearly orthogonal at the channel walls. The mesh extends to infinity upstream and downstream, where the mapping is singular. Special procedures are required to treat the singularities at infinity, including computation of the metrics near those points. Channels with exit areas different from inlet areas are solved; a body with a sting mount is an example of such a case.
    Keywords: AERODYNAMICS
    Type: Langley Symposium on Aerodynamics, Volume 1; p 25-43
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Applications of automatic differentiation in computational fluid dynamics (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Automatic differentiation (AD) is a powerful computational method that provides for computing exact sensitivity derivatives (SD) from existing computer programs for multidisciplinary design optimization (MDO) or in sensitivity analysis. A pre-compiler AD tool for FORTRAN programs called ADIFOR has been developed. The ADIFOR tool has been easily and quickly applied by NASA Langley researchers to assess the feasibility and computational impact of AD in MDO with several different FORTRAN programs. These include a state-of-the-art three dimensional multigrid Navier-Stokes flow solver for wings or aircraft configurations in transonic turbulent flow. With ADIFOR the user specifies sets of independent and dependent variables with an existing computer code. ADIFOR then traces the dependency path throughout the code, applies the chain rule to formulate derivative expressions, and generates new code to compute the required SD matrix. The resulting codes have been verified to compute exact non-geometric and geometric SD for a variety of cases. in less time than is required to compute the SD matrix using centered divided differences.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: The Role of Computers in Research and Development at Langley Research Center; p 168-180
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wall interference assessment/correction (WIAC) for transonic airfoil data from porous and shaped wall test sections (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An existing computational wall interference assessment/correction (WIAC) procedure is applied to two sets of transonic airfoil data obtained from the same model tested in both a porous, planar-wall and a solid, shaped-wall test section. The published airfoil data from the porous test section agrees reasonably well with the published data from the shaped wall test section, although some differences exist. The WIAC procedure is applied to the data to assess and correct any wall interference effects; WIAC corrections generally improve the correlation between the two data sets. As an independent verification, both the published and WIAC corrected airfoil data are compared to Navier-Stokes calculations. Correlations are generally better between the WIAC corrected data and the Navier-Stokes calculations than between similar correlations with the published data.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 90-1406
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Transonic wall interference assessment and corrections for airfoil data from the 0.3-meter TCT adaptive wall test section (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The wall interference assessment/correction code presented is nonlinear, involves four walls, and is applicable to transonic airfoil data from wind tunnels with shaped, solid top and bottom walls. Attention is given to its application to data from the NASA 0.3-m Transonic Cryogenic Tunnel Adaptive Test Section, for two sizes of a NACA 0012 airfoil and to simulated data for an inviscid two-dimensional full-potential code. This study indicates that while adaptive wall wind tunnels significantly reduce some aspects of wall-interference effects (by comparison to straight solid and slotted wall wind tunnels), residual wall and other interference effects are present.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1431
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Multidisciplinary Design Optimization Techniques: Implications and Opportunities for Fluid Dynamics Research (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A challenge for the fluid dynamics community is to adapt to and exploit the trend towards greater multidisciplinary focus in research and technology. The past decade has witnessed substantial growth in the research field of Multidisciplinary Design Optimization (MDO). MDO is a methodology for the design of complex engineering systems and subsystems that coherently exploits the synergism of mutually interacting phenomena. As evidenced by the papers, which appear in the biannual AIAA/USAF/NASA/ISSMO Symposia on Multidisciplinary Analysis and Optimization, the MDO technical community focuses on vehicle and system design issues. This paper provides an overview of the MDO technology field from a fluid dynamics perspective, giving emphasis to suggestions of specific applications of recent MDO technologies that can enhance fluid dynamics research itself across the spectrum, from basic flow physics to full configuration aerodynamics.
    Keywords: Computer Programming and Software
    Type: AIAA Paper 99-3798 , 30th AIAA Fluid Dynamics Conference; Jun 28, 1999 - Jul 01, 1999; Norfolk, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis of Runway Incursion Data (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A statistical analysis of runway incursion (RI) events was conducted to ascertain relevance to the top ten challenges of the National Aeronautics and Space Administration Aviation Safety Program (AvSP). The information contained in the RI database was found to contain data that may be relevant to several of the AvSP top ten challenges. When combined with other data from the FAA documenting air traffic volume from calendar year 2000 through 2011, the structure of a predictive model emerges that can be used to forecast the frequency of RI events at various airports for various classes of aircraft and under various environmental conditions.
    Keywords: Air Transportation and Safety
    Type: AIAA Paper 2013-4400 , NF1676L-16115 , AIAA Aviation Technology, Integration, and Operations (ATIO) Conference; Aug 12, 2013 - Aug 14, 2013; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The Challenges of Credible Thermal Protection System Reliability Quantification (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The paper discusses several of the challenges associated with developing a credible reliability estimate for a human-rated crew capsule thermal protection system. The process of developing such a credible estimate is subject to the quantification, modeling and propagation of numerous uncertainties within a probabilistic analysis. The development of specific investment recommendations, to improve the reliability prediction, among various potential testing and programmatic options is then accomplished through Bayesian analysis.
    Keywords: Quality Assurance and Reliability
    Type: NF1676L-16765 , Paper No. IPPW-10-77 , International Planetary Probe Workshop (IPPW-10); Jun 17, 2013 - Jun 21, 2013; San Jose, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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