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  • 1
    Publication Date: 2004-12-03
    Keywords: GENERAL
    Type: Joint Conf on Lifting Manned Hypervelocity and Reentry Vehicles, part 1; p 73-79
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  • 2
    Publication Date: 2011-08-18
    Description: The solution of the time-dependent, Reynolds-averaged, Navier-Stokes equations for unsteady, interacting flows by finite-difference algorithms is discussed. Specific examples include (1) unsteady transonic flow over a thick biconvex airfoil, (2) determination of buffet boundaries for a transonic lifting airfoil, (3) the simulation of aileron buzz and (4) dynamic stall. Algorithms considered include explicit methods, mixed (or hybrid) methods, and fully implicit methods. Consideration of time scales for computational stability, computational accuracy, and physical accuracy and the use of time-dependent adaptive meshing to realize computational efficiency are also discussed.
    Keywords: AERODYNAMICS
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  • 3
    Publication Date: 2011-08-18
    Description: Previously cited in issue 15, p. 2120, Accession no. A75-33931
    Keywords: AERODYNAMICS
    Type: (ISSN 0001-1452)
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  • 4
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    Publication Date: 2011-08-18
    Description: The ILLIAC IV computer has been programmed with an implicit, finite-difference code for solving the thin layer compressible Navier-Stokes equation. Results presented for the case of the buffet boundaries of a conventional and a supercritical airfoil section at high Reynolds numbers are found to be in agreement with experimentally determined buffet boundaries, especially at the higher freestream Mach numbers and lower lift coefficients where the onset of unsteady flows is associated with shock wave-induced boundary layer separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Nov. 198
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  • 5
    Publication Date: 2011-08-16
    Description: Numerical integration of differential equations governing one dimensional flow of reactive gas, discussing flows of converging-diverging nozzle and normal shock waves
    Keywords: FLUID MECHANICS
    Type: ; ACE(
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  • 6
    Publication Date: 2016-06-07
    Description: The Reynolds averaged Navier-Stokes equations are solved numerically for a variety of transonic airfoil configurations where viscous phenomena are important. Illustrative examples include flows past sensitive geometries, Reynolds number effects, and buffet phenomena.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 119-131
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-13
    Description: Parasitic eigenvalue in integration of equations governing one dimensional flow of chemically reactive gas
    Keywords: FLUID MECHANICS
    Type: COMBUSTION INST. AND U. OF CALIFORNIA, SPECIALISTS'' SESSION ON CHEMICAL KINETICS CALCULATIONS; Oct 30, 1968; BERKELEY, CALIF.
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  • 8
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    Publication Date: 2019-07-13
    Description: An implicit finite-difference computer code that uses a two-layer algebraic eddy viscosity model and exact geometric specification of the airfoil has been used to simulate transonic aileron buzz. The calculated results, which were performed on both the Illiac IV parallel computer processor and the Control Data 7600 computer, are in essential agreement with the original expository wind-tunnel data taken in the Ames 16-Foot Wind Tunnel just after World War II. These results and a description of the pertinent numerical techniques are included.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0134 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
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  • 9
    Publication Date: 2019-07-13
    Description: A generalized hyperbolic marching method employing a nonorthogonal coordinate system and using a split differencing scheme for calculating steady supersonic flow over aerodynamic shapes is presented. It is a second-order-accurate mixed explicit-implicit procedure that solves the inviscid adiabatic and nondiffusive equations for chemically reacting flow in integral conservation-law form. The relationship between the integral and differential forms of the equations are examined and the relative merits of each discussed. The method admits initial Cauchy data situated on any arbitrary surface and integrates them forward along a general curvilinear coordinate, distorting and deforming the surface as it advances. The chemical kinetics term is split from the convective terms which are themselves dimensionally split, thereby freeing the fluid operators from the restricted step-size imposed by the chemical reactions and increasing the computational efficiency. The accuracy of this splitting technique is analyzed, a sufficient stability criterion is established, and comparisons are made with another method.
    Keywords: AERODYNAMICS
    Type: Computational Fluid Dynamics Conference, 2nd; Jun 19, 1975 - Jun 20, 1975; Hartford, CN
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  • 10
    Publication Date: 2019-07-13
    Description: A computer code based on the method of characteristics is described and applied to the study of two- and three-dimensional chemical nonequilibrium flow over sharp and blunt-nosed bodies. Nonequilibrium flow over a wedge is used to show the approach to equilibrium flow, and to demonstrate the nature of the reaction zone behind the bow shock wave. The structure and development of a blunt-body entropy layer in nonequilibrium flow is examined for a blunt cone at zero incidence. Three-dimensional computations for the space shuttle body at 30 deg angle of attack are presented. A nondimensional scaling parameter, the Damkoehler number, which is the ratio of flow time to chemical reaction time, is calculated and its significance discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-835 , American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference; Jun 16, 1975 - Jun 18, 1975; Hartford, CT
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