Transonic aerofoils admitting anomalous behaviour of lift coefficient

Kuzmin, Alexander; Ryabinin, A. N.

doi:10.1017/s0001924000009209

Cited by 4 publications

(4 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1 [6,8]. Also the instability of closely spaced supersonic regions was examine Whitcomb airfoil with a deflected aileron at the Reynolds number Re=5.610 6 [9].…”

Section: Problem Formulationmentioning

confidence: 99%

“…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%

“…Also we considered a time-dependent aileron deflection 2 e of the supersonic regions crucially changes pressure distributions and e airfoil. This phenomenon was scrutinized for a number of symmetric for the asymmetric J-78 airfoil whose upper surface is nearly flat in the lso the instability of closely spaced supersonic regions was examined for a eflected aileron at the Reynolds number Re=5.610 6 [9].…”

Section: Problem Formulationmentioning

confidence: 99%

See 2 more Smart Citations

Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

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.

show abstract

“…1 [6,8]. Also the instability of closely spaced supersonic regions was examine Whitcomb airfoil with a deflected aileron at the Reynolds number Re=5.610 6 [9].…”

Section: Problem Formulationmentioning

confidence: 99%

Section: Problem Formulationmentioning

confidence: 99%

Section: Problem Formulationmentioning

confidence: 99%

See 1 more Smart Citation

Transonic flow past a Whitcomb airfoil with a deflected aileron

Kuzmin¹

2013

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

show abstract

“…Subsequent numerical studies of inviscid and turbulent flow confirmed the abrupt restructuring of 2D flow field due to the coalescence of S-regions at increasing ∞ or their rupture at decreasing ∞ . This phenomenon was scrutinized for a number of symmetric airfoils [10,11] and also for symmetric ones, such as the J-78 airfoil, the Boeing 737 midspan profile [12], and a Whitcomb airfoil with aileron deployments [13]. It was shown that both flow regimes (with the double and merged S-regions) can be either steady or exhibit self-exciting oscillations near the trailing edge due to the instability of the separated boundary layer.…”

Section: Introductionmentioning

confidence: 99%

Sensitivity Analysis of Transonic Flow over J-78 Wings

Kuzmin

2015

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

3D transonic flow over swept and unswept wings with an J-78 airfoil at spanwise sections is studied numerically at negative and vanishing angles of attack. Solutions of the unsteady Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver on unstructured meshes. The numerical simulation shows that adverse Mach numbers, at which the lift coefficient is highly sensitive to small perturbations, are larger than those obtained earlier for 2D flow. Due to the larger Mach numbers, there is an onset of self-exciting oscillations of shock waves on the wings. The swept wing exhibits a higher sensitivity to variations of the Mach number than the unswept one.

show abstract

A multiplicity of regimes of transonic flow in channels with branching

Ryabinin

2021

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

The flow in 2D channel with a flat plate located along the plane of symmetry of the channel at a certain distance from the inlet was numerically studied. Straight segments formed the channel walls. At the inlet and the outlet of the channel, a supersonic flow was set. The first and third parts of the channel diverged. The middle part converged. Solutions to the Euler equations were obtained using the Ansys CFX finite volume solver. Four solutions were found that differed in the position of the shock waves. The hysteresis in the shock wave position versus Mach number given at the inlet was found. In a certain range of the inlet Mach number, there were asymmetric solutions of the equations.

show abstract

Transonic aerofoils admitting anomalous behaviour of lift coefficient

Cited by 4 publications

References 11 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 over J-78 Wings

A multiplicity of regimes of transonic flow in channels with branching

Contact Info

Product

Resources

About