Universal single level implicit algorithm for gasdynamics
C. K. Lombard,E. Venkatapathy,J. Bardina +2 more
- 25 Jun 1984
About: The article was published on 25 Jun 1984. and is currently open access. The article focuses on the topics: Eigenvalues and eigenvectors.
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Citations
Three dimensional hypersonic flow simulations with the CSCM implicit upwind Navier-Stokes method
Jorge Bardina,C. K. Lombard +1 more
- 01 Jan 1987
TL;DR: In this article, the authors extended the Bardina and Lombard (1985) Navier-Stokes method to the simulation of complex hypersonic reentry vehicle external flows at angle of attack, and the robust stability of the method derives from the combination of conservative implicit upwind flux difference splitting with a three-dimensional diagonally dominant approximate factorization and relaxation scheme and characteristic-based implicit boundary approximations.
45
The relation between flux vector splitting and parabolized schemes
C.-L. Chang,C. L. Merkle +1 more
TL;DR: In this article, the relationship between PNS and thin layer Navier-Stokes algorithms is used to develop traditional and new PNS procedures, which are at least as accurate as the more traditional pressure-gradient-split PNS system.
39
Computing of separated flow using the space-marching conservative supra-characteristics method
TL;DR: In this article, the authors used the Conservative Supra-Characteristics Method (CSCM-S) of Lombard to compute surface pressure, heat transfer, and skin friction coefficients for two compression corner cases.
13
Implicit Boundary Treatment for Joined and Disjoint Patched Mesh Systems
C. K. Lombard,Ethiraj Venkatapathy +1 more
- 15 Jul 1985
TL;DR: The CSCM flux difference eigenvector split upwind scheme for the compressible Euler or Navier-Stokes equation is adapted to solve the problem of capturing embedded flow structures with high resolution on systems of aligned overset meshes.
13
Time-iterative solutions of viscous supersonic nozzle flows
TL;DR: In this article, a discretization scheme using upwind flux-vector split differencing in the streamwise direction and central difference in the cross-stream direction is chosen.
11
References
Thin-layer approximation and algebraic model for separated turbulent flows
B. Baldwin,H. Lomax +1 more
- 01 Jan 1978
TL;DR: In this article, an algebraic turbulence model for two-and three-dimensional separated flows is specified that avoids the necessity for finding the edge of the boundary layer, and compared with experiment for an incident shock on a flat plate, separated flow over a compression corner, and transonic flow over an airfoil.
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Transonic flowfield in a supersonic nozzle with small throat radius of curvature.
TL;DR: In this paper, internal flow measurements in transonic region of supersonic nozzle with small throat radius of curvature compared with prediction data were used to estimate the internal flow of a supersonically-charged supersonica nozzle.
151
Calculation of viscous supersonic flows over finned bodies
M. M. Rai,Denny S. Chaussee,Y. M. Rizk +2 more
- 01 Jul 1983
TL;DR: In this paper, the parabolized Navier-Stokes (PNS) equations are used to calculate the viscous, supersonic flow fields about a six-finned projectile and a generic four finned missile at angles of attack.
31
Conservative supra-characteristics method for splitting the hyperbolic systems of gasdynamics with computed boundaries for real and perfect gases
C. K. Lombard,J. Oliger,J. Y. Yang,W. C. Davy +3 more
- 01 Jun 1982
TL;DR: In this article, a globally conservative upwind finite difference method (CSCM) consisting of both implicit interior point and boundary point equations is constructed from a new characteristics based flux difference splitting.
21
Numerical Simulation of Steady Supersonic Viscous Flow
Lewis B. Schiff,Joseph L. Steger +1 more
TL;DR: In this paper, a noniterative, implicit, space-marching, finite-difference algorithm is developed for the steady thin-layer Navier-Stokes equations in conservation-law form.