Non-unique transonic flows over airfoils

Kuzmin, Alexander

doi:10.1016/j.compfluid.2012.04.001

Cited by 26 publications

(24 citation statements)

References 18 publications

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“…The last term in (1b) shifts the rear part of the airfoil upward, simulating an aileron rotation at a small angle θ, as illustrated in Fig. 1 [6,8]. Also the instability of closely spaced supersonic regions was examined for a Whitcomb airfoil with a deflected aileron at the Reynolds number Re=5.610 6 [9].…”

Section: Problem Formulationmentioning

confidence: 99%

“…The ex followed by a coalescence of the supersonic regions crucially changes pressure distributio aerodynamic loads on the airfoil. This phenomenon was scrutinized for a number of sym profiles [6][7], as well as for the asymmetric J-78 airfoil whose upper surface is nearly fla midchord region [6,8]. Also the instability of closely spaced supersonic regions was examin Whitcomb airfoil with a deflected aileron at the Reynolds number Re=5.610 6 [9].…”

Section: Problem Formulationmentioning

confidence: 99%

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Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

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The sensitivity of transonic flow past a Whitcomb airfoil to deflections of an aileron is studied at free-stream Mach numbers from 0.81 to 0.86 and vanishing or negative angles of attack. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the k-ω SST turbulence model. The numerical study demonstrates the existence of narrow bands of the Mach number and aileron deflection angles that admit abrupt changes of the lift coefficient at small perturbations. In addition, computations reveal free-stream conditions in which the lift coefficient is independent of aileron deflections of up to 5 degrees. The anomalous behavior of the lift is explained by interplay of local supersonic regions on the airfoil. Both stationary and impulse changes of the aileron position are considered.

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Section: Problem Formulationmentioning

confidence: 99%

Section: Problem Formulationmentioning

confidence: 99%

Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

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“…This phenomenon was scrutinized for a number of symmetric profiles and an asymmetric J-78 airfoil, the upper surface of which is nearly flat in the midchord region [7]. Also, the flow sensitivity to small perturbations was investigated for a Whitcomb airfoil with upward deflections of an aileron [8].…”

Section: Formulation Of the Problemmentioning

confidence: 99%

“…Both flow regimes (with double and single supersonic regions) can be steady or exhibit slight oscillations due to instability of the separated boundary layer (i.e., a buffet onset, near the trailing edge). This phenomenon was scrutinized for a number of symmetric profiles and an asymmetric J-78 airfoil, the upper surface of which is nearly flat in the midchord region [7]. Also, the flow sensitivity to small perturbations was investigated for a Whitcomb airfoil with upward deflections of an aileron [8].…”

Section: Introductionmentioning

confidence: 99%

Sensitivity analysis of transonic flow past a NASA airfoil/wing with spoiler deployments

Kuzmin¹

2014

International Journal of Aeronautical and Space Sciences

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Transonic flow past a NASA SC(2)-0710 airfoil with deployments of a spoiler up to 6° was studied numerically. We consider angles of attack from -0.6° to 0.6° and free-stream Mach numbers from 0.81 to 0.86. Solutions of the unsteady Reynoldsaveraged Navier-Stokes equations were obtained with a finite-volume solver using several turbulence models. Both stationary and time-dependent deployments of the spoiler were examined. The study revealed the existence of narrow bands of the Mach number, angle of attack, and spoiler deflection angle, in which the flow was extremely sensitive to small perturbations. Simulations of 3D flow past a swept wing confirmed the flow sensitivity to small perturbations of boundary conditions.

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“…In the 2000s, it was demonstrated that the transonic flow around an airfoil with surface of small curvature is sensitive to the changes in the parameters of the free flow [1]. Sensitivity is caused by the interaction of local supersonic regions near the airfoil.…”

Section: Introductionmentioning

confidence: 99%

Bifurcation of Transonic Flow in a Channel With a Central Body

Рябинин¹,

Suleymanov²

2016

Topical Problems of Fluid Mechanics 2016

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Abstract2D transonic flow in a channel of variable cross-section with a central body is studied numerically using a solvers based on the Euler and Reynolds-averaged Navier-Stokes equations. The flow velocity is supersonic at the inlet and outlet of the channel. Between the supersonic regions, there is a local subsonic region. Computations reveal a hysteresis in the shock position versus the inflow Mach number. In the certain range of inlet Mach numbers there are asymmetrical solutions of the equations.

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Non-unique transonic flows over airfoils

Cited by 26 publications

References 18 publications

Transonic flow past a Whitcomb airfoil with a deflected aileron

Transonic flow past a Whitcomb airfoil with a deflected aileron

Sensitivity analysis of transonic flow past a NASA airfoil/wing with spoiler deployments

Bifurcation of Transonic Flow in a Channel With a Central Body

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