Shock wave and centered rarefaction fan in Noble–Abel gas

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Planar supersonic flows of inviscid gas, obeyed the Abel – Noble (AN) equation of state, are considered. Formulas connecting flow parameters of considered gas before and after shock wave are obtained. Solution of Prandtl–Meyer problem for flow of AN gas in centered rarefaction fan is constructed. Critical values of velocity vectors turn angle in oblique shock wave and rarefaction fan are found. Comparisons with corresponding solution for perfect gas are given.

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作者简介

M. Brutyan

Central Aerohydrodynamic Institute named after N.E. Zhukovsky; Moscow Institute of Physics and Technology

编辑信件的主要联系方式.
Email: murad.brutyan@tsagi.ru
俄罗斯联邦, Zhukovsky; Dolgoprudny

U. Ibragimov

Central Aerohydrodynamic Institute named after N.E. Zhukovsky

Email: umar.ibragimov94@yandex.ru
俄罗斯联邦, Zhukovsky

M. Meniailov

Central Aerohydrodynamic Institute named after N.E. Zhukovsky

Email: mickmenn@yandex.ru
俄罗斯联邦, Zhukovsky

参考

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2. Fig. 1. Family of shock adiabats (solid line) and isentropes (dashed line); 1) – ; 2) – ; 3) –

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3. Fig. 2. Maximum value of the ratio ρ2 / ρ1 in the shock adiabat (solid line) and in the isentrope (dashed line)

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4. Fig. 3. Flow diagram in the case of an oblique shock wave

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5. Fig. 4. Velocity diagram for oblique shock wave of gas compression AN: 1) – ; 2) – ; 3) – ; 4) – ; 5) – ; 6) –

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6. Fig. 5. Dependence of the flow rotation angle on the shock wave inclination angle: 1) – ; 2) – ; 3) – ; 4) – ; 5) – ; 6) – ; 7) – line corresponding to the value M=1 behind the shock

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7. Fig. 6. Flow diagram in a centered rarefaction wave

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8. Fig. 7. Dependence of the angle of rotation of the velocity vector in the centered rarefaction wave of gas AH, 1) – b* = 0; 2) – b* = 0.1; 3) – b* = 0.2; 4) – b* = 0.3; 5) – b* = 0.4; 6) – b* = 0.5

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