Drag and lift in nonadiabatic transonic flow

Schnerr, Günter; Dohrmann, Ulrich

doi:10.2514/6.1991-1716

Cited by 10 publications

(10 citation statements)

References 7 publications

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“…The reduction is also an increase in pressure before and after the maximum thickness but the result is a net increase in pressure on the leading edge side which causes the drag to increase. This tendency may be inverted for angle of attack greater than 0 • , see previous work [1]. …”

Section: Resultsmentioning

confidence: 99%

“…It is well known that in adiabatic flow the sweep angle reduces the critical Mach number compared to a straight wing, which reduces drag for the same free stream Mach number. The earlier work of Schnerr [1] showed that for a 2-D NACA-0012 airfoil the drag coefficient increased as humidity increased for zero angle of attack. The 3-D Euler model is based on the work of Benetschik [2].…”

Section: Introductionmentioning

confidence: 99%

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3‐D Inviscid Transonic Condensing Flow around a Swept Wing

Goodheart

Schnerr

2003

Proc Appl Math and Mech

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

3‐D Inviscid Transonic Condensing Flow around a Swept Wing

Goodheart

Schnerr

2003

Proc Appl Math and Mech

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“…Young [24] provided the fundamental equations for accurate calculation of gas-droplet multiphase flows. The numerical results presented in this article have been obtained using the vectored scheme described by Schnerr and Dohrmann [25] and by Adam and Schnerr [26].…”

Section: Self-excited Oscillations In Laval Nozzlesmentioning

confidence: 99%

Unsteadiness in Condensing Flow: Dynamics of Internal Flows with Phase Transition and Application to Turbomachinery

Schnerr

2005

Proceedings of the Institution of Mechanical Engineers, Part C:

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Steady flows of condensable fluids may become unsteady if one component of the fluid starts to condense. In high-speed expansion flows, typical for large-scale steam turbines, the subcooled vapour state collapses after nucleation, typically in flow regimes close to Mach number 1. After the formation of steady shocks, instantaneous thermal choking initiates selfexcited high-frequency oscillations which is the focus of this article. The driving mechanism is the interaction of compressibility and energy supply in flows close to maximum mass flux density and is therefore not controlled by the viscosity of the fluid. Additional viscosity-driven excitation mechanisms exist and superpose the primary diabatic instability, especially in axial cascades. Typical are shedded shear layers from blade trailing edges and the periodic interference of wakes separating from the stator with the rotor blades. This article presents a review of the authors and various co-workers' research, supplemented by important references to complete the subject under consideration. This article starts with an introduction in the most simple flow model of given heat addition in constant area flow and ends with mixed homogeneous/heterogeneous condensation in a transonic axial cascade stage with a high-resolution sliding interface for preservation of submicron condensate convected from the stator into the rotor. Numerical simulations are compared with experiments of flows with and without carrier gas.

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“…Transonic moist air flow with non-equilibrium condensation was conducted by Rusak and Lee [7], Schnerr and Dohrmann [10,11], and Doerffer and Szumowski [12]. From these experiments, it was observed that the shock wave structure and shockinduced separation were sensitive to relative humidity variations.…”

Section: Introductionmentioning

confidence: 99%

“…From these experiments, it was observed that the shock wave structure and shockinduced separation were sensitive to relative humidity variations. However, depending on the airfoil geometry and heat supply conditions, the pressure drag around the airfoil can be reduced to the classic dry air case at the same Mach number [10,11]. Recently, transonic shock waves-boundary layer interaction over a wall-mounted bump under various humid conditions was investigated experimentally by Huang et al [13].…”

Section: Introductionmentioning

confidence: 99%

Transonic Moist Air Flow around a Symmetric Disc Butterfly Valve with Non-Equilibrium Condensation

Hasan

Matsuo

Setoguchi

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part C:

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Transonic flow around a symmetric disc butterfly valve is associated with the appearance of shock waves on valve surfaces. In this case, the interaction between shock waves and boundary layers becomes complex and thus generates the flow-induced aerodynamic instability. In the transonic or supersonic flow where vapour is contained in the main flow, the rapid expansion of the flow may give rise to non-equilibrium condensation. In the present study, the effect of non-equilibrium condensation of moist air on the shock-induced flow field oscillation around a butterfly valve was investigated numerically. The results showed that in cases with non-equilibrium condensation, the flow field aerodynamic instabilities such as root mean square of pressure oscillation and shock-induced oscillation frequency are reduced significantly compared with those without the non-equilibrium condensation. Moreover, the total pressure loss increases and the vortex shedding frequency is reduced with non-equilibrium condensation.

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Drag and lift in nonadiabatic transonic flow

Cited by 10 publications

References 7 publications

3‐D Inviscid Transonic Condensing Flow around a Swept Wing

3‐D Inviscid Transonic Condensing Flow around a Swept Wing

Unsteadiness in Condensing Flow: Dynamics of Internal Flows with Phase Transition and Application to Turbomachinery

Transonic Moist Air Flow around a Symmetric Disc Butterfly Valve with Non-Equilibrium Condensation

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