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  • 1
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    Use of risk projection models to estimate mortality and incidence from radiation-induced breast cancer in screening programs (2005)
    Institute of Physics
    Details
    Publication Date: 2005-01-20
    Print ISSN: 0031-9155
    Electronic ISSN: 1361-6560
    Topics: Biology , Medicine , Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Vortex breakdown simulation based on a nonlinear inviscid model (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: It is shown that the inviscid equations governing steady axisymmetric flow with swirl, admit solutions with closed streamlines. Results are obtained using two different numerical algorithms. The first is based on a multigrid method for nonlinear eigenvalue problems, while the second is based on a least squares formulation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Euler and Navier-Stokes solutions for supersonic shear flow past a circular cylinder (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 583-587
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Far-field boundary conditions for transonic lifting solutions to the Euler equations (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Far-field boundary conditions for the Euler equations are formulated and applied to transonic lifting flow over an airfoil in an unbounded domain. An expansion of the linearized small-disturbance equation in the far field is developed and the leading-order term, corresponding to a point vortex representation for the airfoil, is retained. A comprehensive evaluation across the Mach number range of the procedure's effectiveness in eliminating dependence of the numerical results on the boundary extent is presented. Extension of the method to three dimensions is also outlined.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1074-108
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Stability of shock waves attached to wedges and cones (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 06, p. 799, Accession no. A82-17876
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1611-161
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Airfoil optimization by the one-shot method (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: An efficient numerical approach for the design of optimal aerodynamic shapes is presented in this paper. The objective of any optimization problem is to find the optimum of a cost function subject to a certain state equation (Governing equation of the flow field) and certain side constraints. As in classical optimal control methods, the present approach introduces a costate variable (Language multiplier) to evaluate the gradient of the cost function. High efficiency in reaching the optimum solution is achieved by using a multigrid technique and updating the shape in a hierarchical manner such that smooth (low-frequency) changes are done separately from high-frequency changes. Thus, the design variables are changed on a grid where their changes produce nonsmooth (high-frequency) perturbations that can be damped efficiently by the multigrid. The cost of solving the optimization problem is approximately two to three times the cost of the equivalent analysis problem.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Optimum Design Methods for Aerodynamics; 21 p
    Format: text
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  • 7
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    Breakdown of the conservative potential equation (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The breakdown of the conservative potential approximation occurs for all the airfoils tested. It develops as soon as the shock waves appear in the flow field. Since shock waves are not properly represented by the potential approximation, it is conjectured that the breakdown is due to the isentropic shock jump condition of the potential approximation.
    Keywords: AERODYNAMICS
    Type: Langley Symposium on Aerodynamics, Volume 1; p 45-71
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Numerical study of flowfields about asymmetric external conical corners (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 17, p. 3111, Accession no. A80-41562)
    Keywords: AERODYNAMICS
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  • 9
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    Foundations for the numerical solution of the Euler equations (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The Navier-Stokes equations represent an extremely good model of the physical phenomena encountered in most aeronautical problems. However, the computational resource needed to solve the Navier-Stokes equations are so large that even with today's supercomputers, it is necessary to make use of simpler models. A large number of external aerodynamic problems can be accurately described by a simpler model. This model consists of an outer inviscid flow plus a boundary-layer thickness correction for the vehicle shape. The outer inviscid model may be represented by the potential equation or by the Euler equation. The present paper provides the foundations for the numerical solution of the Euler equations. The governing equations are considered, taking into account conservation laws, the medium, the differential form of the conservation laws, generalized solutions, shock-fitting, and characteristics. Attention is also given to initial and boundary conditions, existence and uniqueness, and rotational phenomena.
    Keywords: AERODYNAMICS
    Format: text
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  • 10
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    Nonunique solutions to the transonic potential flow equation (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Steinhoff and Jameson (1981) have shown that within a certain range of angle of attack and freestream Mach number, numerical solutions of the full-potential equation for flow past an airfoil are not unique. This study was mainly concerned with showing that the anomaly is inherent to the partial-differential equation governing the flow and not a result of its discrete representation. Steinhoff and Jameson conjectured that the anomaly may have a physical basis. The present investigation has two objectives. Results are to be presented which indicate that the anomaly is due to a breakdown in the potential approximation, rather than a phenomenon associated with the inviscid flowfield. The second objective is to show that the lift coefficient, predicted by the potential equation, is a smooth but multivalued function of the angle of attack.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 145
    Format: text
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