Wind tunnel testing of adaptive wing/aircraft structures has been carried out at TSAGI with the aim of investigating, demonstrating and assessing novel concepts, enabling cost-effective aerodynamic designs through the use of adaptive/morphing wings, and weight reduction through the realization of smart structures and the use of aeroelastic deflections. Relevant examples of performed researches activities have been presented in this chapter thus providing a general overview of the adopted experimental approaches and obtained results.

Wind Tunnel Testing of Adaptive Wing Structures

The experiments described in this paper were performed in the ETW cryogenic wind tunnel in February 2014 using the NASA Common Research Model to investigate slotted wall interference effects and form a test case for the verification and validation of relevant CFD tools. These tests were performed in the frame of the ESWI project funded by the European Commission in the 7 framework program. The EWT-TsAGI software with a cryogenic solver is described. Analyses of distributions of the wall pressure coefficient are presented along with comparisons with CFD results.

Slotted Wall Interference Investigation in ETW using the NASA CRM model

This paper is devoted to the assessment of wall interference in the slotted wall test section of the European Transonic Windtunnel (ETW) over a wide range of Reynolds numbers. The experimental part of the investigation was performed in February 2014 by testing the NASA Common Research Model mounted on a fin-sting support. These tests were carried out within the scope of the ESWIRP project funded by the European Commission in the 7th framework program. The numerical research was based on the Electronic WindTunnel (EWT-TsAGI) software with a cryogenic solver. The assessed Mach number influence on the wall signatures revealed a very similar effect to applying the classical Prandtl–Glauert rule over the investigated Mach number range. Practically, no Reynolds number effects on the wall pressure distributions generated by the model and its support system could be identified over the wide range of Re numbers investigated. The first attempt of the EWT-TsAGI code application for a simulation of ETW tests featuring the model in the slotted wall tunnel showed a fair coincidence of the pressure coefficient distribution on test section walls in the model region, on the wing-root sections and the drag polar at moderate lift coefficient values.

A numerical approach for assessing slotted wall interference using the CRM model at ETW

This work is devoted to the validation of modern differential models of turbulence for the calculation of separation in a supersonic flow around the compression wedge. Use is made of the data of experiments for the 25° wedge made by A.A. Zheltovodov at the Khristianovich Institute of Theoretical and Applied Mechanics (ITAM), Siberian Branch (SB), Russian Academy of Sciences (RAS). These data are compared to the results of the three-dimensional and two-dimensional calculations by the use of several differential models of turbulence. A modification of the SST model is proposed that yields an improvement in the quality of the description of the separation zone. The three-dimensional structure of the separation on the wedge is analyzed.

On the accuracy of numerical simulation of the boundary layer separation on a finite-width wedge

To obtain accurate data of calculation method error requires detailed simulation of the experiment in wind tunnel with keeping all features of the model, installation and gas flow. Two examples of such detailed data comparison are described in this paper. The experimental characteristics of NASA CRM model obtained in the ETW wind tunnel (Cologne, Germany), and CFD characteristics of this model obtained with the use of EWT-TsAGI application package are compared. Following comparison is carried out for an airplane model in the T-128 wind tunnel (TsAGI, Russia). It is seen that deformation influence on integral characteristics grows with increasing Re number and, accordingly, the dynamic pressure. CFD methods application for problems of experimental research in the wind tunnel allows to separate viscosity and elasticity effects.

Egor Vyacheslavovich Kazhan

Papers

Stability improvement of godunov-kolgan-rodionov tvd scheme by a local implicit smoother

Estimation of operating conditions of a mid-range aircraft auxiliary power unit with receiver inlet in turbulent flow