Computational tools for supporting the testing of civil aircraft configurations in wind tunnels

Progress in Flight Physics – Volume 7

Kursakov

Mikhaylov

et al. 2015

Self Cite

Zonal approach for unsteady Reynolds-averaged Navier Stokes (URANS) problem solution is described. Original feature of this approach is to use Courant Friedrichs Levi number CFL ∼ 1 in the main part of calculation domain excluding thin part of boundary layer. It is achieved by using explicit numerical scheme with fractional time stepping in the main part of calculation domain. In the near-wall zone of boundary layer, implicit dual stepping method is used. In addition to zonal approach, fully implicit method with dual stepping technology is also implemented. The methods are veri¦ed in comparison with the results of test case data obtained by consortium participants within DeSiReH FP-7 project.

Section: Methodsmentioning

confidence: 99%

“…Such schemes may be considered as standard for calculations of stationary §ows. For scalar model (1), this scheme may be represented in the following form:…”

Section: Methodsmentioning

confidence: 99%

Calculations of unsteady flows around high-lift configurations based on a zonal approach

Progress in Flight Physics – Volume 7

Kursakov

Mikhaylov

et al. 2015

Self Cite

“…To maintain time accuracy, multiple local time steps are taken in the smaller cells. This idea was ¦rst published in [5] and is illustrated in Fig. 1.…”

Section: Description Of the Methodology For The Computational Toolsmentioning

confidence: 99%

Aerodynamic performance of the DeSiReH high-lift laminar wing at free flight and ETW in-tunnel conditions

Progress in Flight Physics – Volume 7

Kazhan

Kursakov

et al. 2015

Self Cite

The current research concerns a half-model high-lift con¦guration inside the European Transonic Wind Tunnel (ETW) at landing regime. The in §uence of the wind-tunnel walls (both slotted and closed) is investigated and the numerical results are compared with measured data. The investigated model is a three-element landing con¦guration with Krueger device and §ap. All calculations are performed on structured grids using EWT-TsAGI code. The computed in-tunnel results are in good agreement with uncorrected experimental data, with maximum lift predicted at the same angle of attack. The slotted wall con¦guration produces less wall interference than the closed wall con¦guration.

“…In the flow potential core the Laplace problem was solved (method of singularities [29] and integral method [30]). By means of the EWT software package [31,32], the limit Mach number for the applica bility of fast linear methods was determined. It was proved that for a moderate degree of the test section blockage the linear methods can be applied up to M = 0.9.…”

Section: Introductionmentioning

confidence: 99%

“…Special codes have been developed to simulate the experiment in TsAGI's wind tunnels T 104 and T 131. Interesting results were obtained by the efforts on the creation of the mathematical model of the European Transonic Windtunnel (ETW) with slotted walls [32]. This work was carried out with support from J.…”

Section: Introductionmentioning

confidence: 99%

The use of computational fluid dynamics in TsAGI experimental works

Math Models Comput Simul

Akinfiev

Власенко

et al. 2012

The paper describes methods to calculate the flow around an aircraft model in a wind tun nel. It formulates special boundary conditions to achieve the necessary flow parameters in the control section, as well as to simulate some features of wind tunnel walls, for example, perforation. In order to accelerate the numerical solution convergence, a method for implicit smoothing is suggested allowing the calculation duration to be reduced several times. The cases of practical use of this methodology are given. It is shown that in the conditions of the TsAGI subsonic wind tunnel, it is possible to simulate the effect on the model from the elements of the structure that are missing in this tunnel, for example, the running track. A mathematical model of the European Transonic Windtunnel (ETW) with slotted walls is presented. It is shown that the flow in the reentry affects the main flow in the test section of this tunnel. Data on the effect of the model support in the TsAGI wind tunnel T 128 are given. The pen iche height used in the half model tests has been justified. The conclusion is made that the mathemat ical model of the wind tunnel is an obligatory part in experimental studies.