Allowance for Gas Compressibility in the γ-Model of the Laminar–Turbulent Transition


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Abstract

The formulation and applicability range of the \(\gamma \)-model of laminar–turbulent transition are analyzed. Its implementation in the EWT-TsAGI application package and verification results for the problem of computing a transitional boundary layer on a plate are described. The cases of zero and adverse pressure gradients are considered. A modification of the \(\gamma \)-model that takes into account the effect of compressibility on the laminar–turbulent transition location is proposed. Two problems are considered to calibrate and test the correction term: the flow over the LV6 laminar-flow airfoil and the flow over the nacelle of a bypass turbojet engine. It is shown that, with the used of the proposed correction, the laminar–turbulent transition location can be correctly predicted in transonic flow regimes.

About the authors

E. S. Matyash

Central Aerohydrodynamic Institute (TsAGI), National Research Center “Zhukovsky Institute”

Email: andrey.savelyev@tsagi.ru
Russian Federation, Zhukovskii, Moscow oblast, 140180

A. A. Savelyev

Central Aerohydrodynamic Institute (TsAGI), National Research Center “Zhukovsky Institute”

Author for correspondence.
Email: andrey.savelyev@tsagi.ru
Russian Federation, Zhukovskii, Moscow oblast, 140180

A. I. Troshin

Central Aerohydrodynamic Institute (TsAGI), National Research Center “Zhukovsky Institute”

Email: andrey.savelyev@tsagi.ru
Russian Federation, Zhukovskii, Moscow oblast, 140180

M. V. Ustinov

Central Aerohydrodynamic Institute (TsAGI), National Research Center “Zhukovsky Institute”

Email: andrey.savelyev@tsagi.ru
Russian Federation, Zhukovskii, Moscow oblast, 140180

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