Validatable Shock-Wave/Turbulent Boundary-Layer Interaction over a Compliant Panel

Shock-Wave/Turbulent-Boundary Layer Interactions (SWTBLI) often occur in applications of technological interest. The associated inherent low-frequency unsteadiness dictates the use of Large-Eddy Simulation (LES) approaches to resolve the interaction, which unavoidably implies a very high computational cost. For this reason, no well-resolved long...

Investigation on inviscid flow methods for 2D LEI tube kite

On a typical 2D LEI kite profile, ow separation is expected to occur on both suction and pressure sides of the airfoil. This thesis is aimed to study various inviscid ow models that are capable of modeling such multiple ow separation phenomena. Inviscid models are capable of modeling single ow separation region over typical airfoils. In these...

A Mach-uniform algorithm: Coupled versus segregated approach

A Mach-uniform algorithm is an algorithm with a good convergence rate for any level of the Mach number. In this paper, the severe time step restriction for low speed flows is removed by treating the acoustic and diffusive terms implicitly. After identification of these terms in the conservative set, we end up with a semi-implicit system. The way...

Numerical schemes for compressible flow with all Mach numbers

This work is concerned with the numerical solution of an inviscid compressible flow. Our goal is to develop a sufficiently accurate and robust method allowing the solution of problems with a wide range of Mach numbers. The main ingredients are the discontinuous Galerkin finite element method (DGFEM), semi-implicit time stepping, special...

Clebsch variable model for unsteady inviscid transonic flow with strong shock waves

In comparison with Euler methods unsteady inviscid transonic full potential methods are known to suffer from limitations with respect to the modeling of shock waves. In this paper unsteady 2D and 3D full potential methods are extended with the Clebsch variable model. This model represents exactly the shockgenerated entropy and vorticity. The...

Numerical simulation of leading-edge vortex flow

An analysis is presented of results of a computational method to simulate the steady compressible vortical type of flow around a 65-deg sharp-edged cropped delta wing. The discussion emphasizes some more fundamental aspects of the numerical simulation such as the separation of the flow, the structure of the leading-edge vortex core and the flow...

TULIPS: A method to calculate transonic potentional flow about oscillating airfoils

A description is given of TULIPS - a method for Transonic Unsteady Lifting Inviscid Potential-flow Simulation. The Mathematical formulation and the numerical approach are presented for flow about oscillating airfoils. TULIPS is based on the numerical integration of the unsteady full-potential equation in generalized coordinates. The equation is...

VISIAN: a viscous-inviscid strong-interaction analysis system

A description is given of VISIAN - a simulation method for 2-D viscous flows with strong viscous-inviscid interaction. The mathematical mode and the numerical algorithm are presented. VISIAN has been coupled with the inviscid-flow solver TRAPS. Results are shown for a number of airfoils; a comparison is made with results from other computations...

A quasi-simultaneous calculation method for strongly interacting viscous flow around an infinite swept wing

An outline is presented of a new code, called VISIAN, for the analysis of aerodynamic flows with strong viscous-inviscid interaction. The code is based on the recently developed quasi-simultsuieous method for the calculation of strongly interacting boundary layers. The feasibility of this method has already been demonstrated liy means of a...

A calculation method of the viscous flow around multi-component airfoils

The viscous flow around multi-component airfoils has been calculated by solving incompressible potential flow and boxindary layer problems iteratively. The potential flow problem is solved by a revised version of the 2D NLR panel method. A model transport equation of turbulent stress is employed to calculate the turbulent boundary layer. The...

Modified version of LTRAN2; a calculation method for inviscid transonic flow about thin airfoils in moderately slow unsteady motion

A method is discussed for the calculation of inviscid transonic flow about thin airfoils in moderately slow unsteady motion. It is an extension of a method which was developed by Ballhaus and Goorjian of NASA Ames and which is applicable for strictly slow unsteady motions only. The modifications involve extra unsteady terms in the boundary...

Program for the computation of axisymmetric supersonic flow around launch type vehicles, based on the method of characteristics

In this report a program in ALGOL (CDC-3300, MBOS (3,2) operating system) is described for the computation of the supersonic flow of a thermally and calorically perfect gas around axisymnetric bodies. Computational details are given and some numerical results are presented. Emphasis is placed on the organization of the program. For a specific...