Die Herausgeber sind Sprecher des EU-Projekts ETMA

Stimmen die Simulationen?

1: Mixing Layers.- Test Case 1: supersonic mixing layers.- Numerical simulation and modeling of an unsteady supersonic mixing-layer flow.- A modified k-? model derived by homogenization techniques.- Compressibility models applied to supersonic mixing layers.- Numerical simulation of supersonic mixing layers at different convective Mach numbers with a k-? model.- Supersonic mixing layer.- Synthesis on compressible mixing layers.- 2: Compressible Back-Step Flow.- The supersonic flow over an axisymmetric rearward facing step Synthesis of results.- Computation of an axisymmetric supersonic back-step flow using a pointwise k-k2/? turbulence model.- Supersonic rearward-facing step calculations using an explicit fractional-step method and a two-equation turbulence model.- 3: Incompressible Wall Flows with Separation.- Presentation of test cases TC-2A TC-2B TC-2C TC-2D two-dimensional incompressible wall flows with separation.- Incompressible recirculating flows, TC2-A low-Re backward-facing step, TC2-B high-Re backward-facing step.- Computational results on test cases TC-2C and TC-2D two dimensional, incompressible flows with recirculation.- Incompressible recirculating flows, TC-2C fence-on-a- wall, TC-2D obstacle-in-channel.- Numerical solution of the turbulent flow over a fence using two equation models.- Computations of separating and reattaching flows with high- and low-Reynolds-number second moment closure.- Incompressible recirculating flows, a critical comparison of computations for low-and~high-Reynolds number flow over a backward-facing step.- Synthesis of test cases TC-2C and TC-2D, two dimensional, incompressible flow past wall-mounted obstacles.- 4: Flows Past a Flat Plate.- Specification of test case TC3 flat plate boundary layers.- A numerical evaluation of anew algebraic turbulence model.- Flat plate boundary layers.- Application of turbulence models to incompressible boundary layers in aeronautics.- The Samuel-Joubert test case, computed by a boundary-layer method.- Application of the finite element method to the Reynolds-averaged Navier-Stokes equations.- Simulations of compresible turbulent boundary layer using a low Reynolds k-? model.- Solutions of non-equilibrium wall boundary layers with a low-Reynolds-number second moment closure.- Synthesis on test case TC3 ETMA workshop, flate plate boundary layers.- 5: Shock Reflection.- ETMA test case 6au]shock reflection on a flat plate: description of the test case.- Numerical simulation of shock reflection with a compressible k-? model.- Simulations of shock reflection on flat plate using a low-Reynolds k-? model.- Assessment of a one-equation pointwise turbulence model for compressible flow - test case TC6.- ETMA test case 6, shock reflection on a flat plate: synthesis of the calculations.- 6: Ramp Flow.- Supersonic compression ramp flow: synthesis of results.- Study of the supersonic compression ramp flow using the k-? turbulence model with and without algebraic Reynolds stress modifications.- Numerical simulation of compression ramp flows with a compressible k-? model.- Computation of a shock-wave boundary-layer interaction on compression ramp flow configuration.- The shock/turbulent boundary layer interaction over the Princeton 20° and 24° ramps.- Computations on the compression ramp using explicit algebraic Reynolds stress models.- Numerical simulation of a 24° compression ramp by a k-? model with compressibility terms.- 7: Flow Over a Bump.- Test case TC5: two dimensional transonic bump.- Assessment of a one-equation pointwise turbulence model forcompressible flow.- Numerical simulation of the flow over a 2D transonic bump with extended separation.- Calculation of a two dimensional transonic bump with a multiple-time-scale turbulence model.- Computation of a two dimensional transonic bump flow using a point wise k-k2/? turbulence model.- Extension of an incompressible algorithm for compressible flow calculations: validation on a transonic flow in a bump.- Computation of a shock wave boundary layer interaction in a nozzle with different anisotropic turbulence models.- 2-D transonic bump flow calculations using an explicit fractional-step method.- Computations on the transonic bump using explicit algebraic Reynolds stress models.- TC5 synthesis.- 8: Steady Airfoil Flow.- Presentation of TC8: flow around airfoil (steady).- Transonic Navier-Stokes computations on unstructured grids using a differential Reynolds stress model.- Implicit multigrid computations of an airfoil flow.- Unstructured grid solutions using k-? with wall functions.- The Dornier 2D Navier-Stokes approach applied to transonic airfoil flow.- Flow calculations past RAE 2822 and MBB-A3 airfoils for the ETMA workshop using the Navier-Stokes code ARC2D.- Calculation of the RAE2822 transonic airfoil using the k-? model.- Application of an unstructured grid flow solver to compressible turbulent flows.- 9: Unsteady Airfoil Flow.- Presentation of the test-case TC8bis.- rediction of the unsteady transonic turbulent flow around a circular-arc aerofoil.- Unsteady separated turbulent flows computation with wall-laws and k-? model.- Unsteady flow over a circular arc airfoil.- Synthesis on the unsteady transonic flow around a circular-arc aerofoil (TC8bis).- Elements Of Synthesis and Conclusion.- Elements Of Synthesis and Conclusion.

The computation of complex turbulent flows by statistical modelling has already a long history. The most popular two-equation models today were introduced in the early sev enties. However these models have been generally tested in rather academic cases. The develope ment of computers has led to more and more acurate numerical methods. The interactions betwe~n numerical and modelling techniques are generally not well mastered. Moreover, computation of real life cases, including 3D effects, complex geometries and pressure gra dients based on two-equation models with low-Reynolds treatment at the proximity of walls are not really of common use. A large number of models has been proposed; this is perhaps the sign that none of them is really satisfactory, and then the assessment of their generality is not an easy task: it requires a lot of understanding of the physics and a lot of work for testing the large number of relevant cases in order to assess their limits of validity which is a condition for an improved confidence in engineering applications. This is probably why workshops and working groups are frequent and the ETMA consor tium has choosen to build a state of the art in theoretical and numerical statistical turbu lence modelling for real life computations by taking some marks with respect to previous workshops such as the Stanford meetings (1980,1981); some problems are kept or updated by new experiments, some problems are discarded, some new problems are introduced; the focus is kept on flows with 2D geometries.