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  • 1
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    A general perturbation approach for computational fluid dynamics (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1748-175
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A general perturbation approach for the equations of fluid dynamics (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An efficient numerical technique to produce accurate solutions to the equations of fluid dynamics is presented where the governing equations are perturbed about an approximate solution and solved by finite-difference methods on a coarsened grid. The result is a scheme which substantially reduces the number of grid points necessary to accurately resolve the flow. Applications are presented for the two-dimensional Euler equations perturbed about a solution of the transonic full potential equation. However, the concept is applicable to arbitrary equation sets, higher dimensions and for a wide variety of applications.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1903 , Computational Fluid Dynamics Conference; Jul 13, 1983 - Jul 15, 1983; Danvers, MA
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    NASA TECHNICAL REPORTS
  • 3
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    Perturbation Method for Computational Fluid-Dynamical Equations (1986)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Description: Perturbation technique yields accurate flow solutions using as few as one-fourth number of grid points required by finite-difference methods. Technique originally developed to solve Euler equations of two-dimensional, steady, inviscid transonic flow about airfoils, applicable to arbitrary equation sets and higher dimensions. New perturbations scheme used in design cycle where potential solutions generated routinely; Euler perturbation method used in second-cut analysis. Method also used to couple other equation sets.
    Keywords: MECHANICS
    Type: ARC-11550 , NASA Tech Briefs (ISSN 0145-319X); 10; 5; P. 98
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    NASA TECHNICAL REPORTS
  • 4
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    Implicit unsteady transonic airfoil calculations at supersonic freestreams (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The computer code LTRAN2 has been extended to compute unsteady transonic flows about oscillating airfoils with supersonic freestreams. The LTRAN2 code uses an alternating direction implicit (ADI) algorithm to solve the two-dimensional, nonlinear, low-frequency, transonic small-disturbance (LF-TSD) equation. The modified code, LTRAN2-SS, includes a 'high-frequency' option. Steady solutions are checked against those computed by the steady TSD code, TSFOIL; unsteady computations of the linear LF-TSD equation are compared with known linear theory solutions; and new unsteady nonlinear solutions are presented. These cases include standard AGARD test cases for the NLR 7301, MBB-A3, and DO Al supercritical airfoils, as well as several NACA airfoils. The modified code enables aerodynamicists to quickly and efficiently compute transonic flows for both subsonic and supersonic freestreams, and thus resolve flutter boundaries through the full extent of the transonic dip phenomenon.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0934 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
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