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

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Abstract

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.

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Abbreviations

B :

Wing span

BTWT:

Boeing Transonic Wind Tunnel

c :

Mean aerodynamic chord

C D :

Drag coefficient

CDV = C D − C 2L /π/λ :

Profile drag coefficient

CEAS:

Council of European Aerospace Societies

CFD:

Computational fluid dynamics

C L :

Lift coefficient

Cp:

Pressure coefficient

CRM:

NASA Common Research Model

DLR:

German Aerospace Center

E :

Young’s modulus

ETW:

European Transonic Wind Tunnel

ESWIRP:

European strategic wind tunnels improved research potential—so-called targeted approach of the Integrating Activities of the FP7 Capacities Work Program

HTP:

Horizontal tail plane of the model

EWT-TsAGI:

Electronic Wind Tunnel, computer code

ICAS:

Institute of Thermomechanics of the Academy of Sciences of the Czech Republic

JAXA:

Japan Aerospace Exploration Agency

M :

Mach number

NASA:

National Aeronautics and Space Administration

NTF:

National Transonic Facility (NASA)

ONERA:

The French aeronautics, space and defense research lab

P, P t :

Total pressure

PETW:

Pilot European Transonic Windtunnel

q :

Dynamic pressure

R :

Coefficient in boundary condition

Re :

Reynolds number

S :

Wing reference area

SPT:

Stereo pattern tracking (ETW system for deformation measurements)

T tot, T t :

Total temperature

TR-PIV:

Time resolved particle image velocimetry

TsAGI:

Central Aerohydrodynamic Institute

u :

Perturbed longitudinal velocity component

UCAM:

University of Cambridge

VKI:

von Karman Institute for Fluid Dynamics, Belgium

VZLU:

Aerospace research and test establishment, Czech Republic

v :

Perturbed normal velocity component

x, y, z :

Coordinates (starting from test section inlet, centreline)

α :

Model angle of attack (°)

Λ :

Wing aspect ratio

η :

Dimensionless (y/b) span-wise pressure orifices location

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Authors and Affiliations

  1. Central Aerohydrodynamic Institute, Zhukovsky, Moscow Region, 140180, Russia

    I. A. Kursakov, A. R. Gorbushin, S. M. Bosnyakov, S. A. Glazkov, A. V. Lysenkov, S. V. Matyash & A. V. Semenov

  2. European Transonic Windtunnel GmbH, 51147, Cologne, Germany

    J. Quest

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  1. I. A. Kursakov
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  2. A. R. Gorbushin
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  3. S. M. Bosnyakov
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  4. S. A. Glazkov
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  5. A. V. Lysenkov
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  6. S. V. Matyash
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  7. A. V. Semenov
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Correspondence to A. R. Gorbushin.

Additional information

This paper is based on a presentation at the CEAS Air & Space Conference 2015, September 7–11, Delft, The Netherlands

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Kursakov, I.A., Gorbushin, A.R., Bosnyakov, S.M. et al. A numerical approach for assessing slotted wall interference using the CRM model at ETW. CEAS Aeronaut J 9, 319–338 (2018). https://doi.org/10.1007/s13272-017-0248-1

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