Transonic Flow about a Thick Circular-Arc Airfoil

McDevitt, John B.; Levy, Lionel L.; Deiwert, George S.

doi:10.2514/3.61402

Cited by 183 publications

(52 citation statements)

References 2 publications

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“…The selected parameters are the same as those performed in experiments (e.g. McDevitt et al 1976;Levy 1978;Marvin et al 1980). The relevant experimental data will thus be employed to validate the present calculation.…”

Section: Computational Overview and Validationmentioning

confidence: 99%

“…To validate the present simulation, we compare numerical results and experimental data (McDevitt et al 1976;McDevitt 1979;Marvin et al 1980) in terms of the frequency of shock motion, averaged pressure coefficient, mean velocity and turbulent shear stress, as well as some quantities related to the shock wave motion, which will be shown in the following section. Assessments of the effect of time step are performed on the calculated solutions.…”

Section: Validationmentioning

confidence: 99%

“…As the flow considered here has a high Reynolds number Re ∼ O(10 7 ) (McDevitt et al 1976;Levy 1978;Marvin et al 1980), the methodology used is a significant issue in numerical simulations. Recent advances in the DES have provided a powerful tool for studying high-Reynolds-number flows and have comprehensively been surveyed by Spalart (2009).…”

Section: Introductionmentioning

confidence: 99%

“…Tijdeman & Seebass (1980) have classified the shock wave motions as being of three types, i.e. type A, B and C. Previous experimental studies of transonic flow over an 18 % thick circular-arc aerofoil at zero incidence have indicated that upstream-propagating shock waves occur alternately on the upper and lower surfaces for a certain range of the free-stream Mach number (McDevitt, Levy & Deiwert 1976;Levy 1978;McDevitt 1979;Marvin, Levy & Seegmiller 1980), which belongs to type C. Moreover, some numerical simulations have been performed using the time-dependent twodimensional Reynolds-averaged Navier-Stokes (RANS) equations with turbulence models (e.g. Marvin et al 1980;Rumsey et al 1996;Xiao, Tsai & Liu 2003).…”

Section: Introductionmentioning

confidence: 99%

“…The present work investigates the compressible flow past an 18 % thick circular-arc aerofoil for a free-stream Mach number M ∞ = 0.76 and a Reynolds number Re = 1.1 × 10 7 , corresponding to experiments (McDevitt et al 1976;Levy 1978;McDevitt 1979;Marvin et al 1980). The three-dimensional Favre-averaged compressible Navier-Stokes equations are solved numerically by means of a finitevolume approach (Lu et al 2005) combined with shock capture technique (Hill, Pantano & Pullin 2006).…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Numerical investigation of the compressible flow past an aerofoil

Chen

2009

J. Fluid Mech.

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Numerical investigation of the compressible flow past an 18% thick circular-arc aerofoil was carried out using detached-eddy simulation for a free-stream Mach number M∞ = 0.76 and a Reynolds number Re = 1.1 × 107. Results have been validated carefully against experimental data. Various fundamental mechanisms dictating the intricate flow phenomena, including moving shock wave behaviours, turbulent boundary layer characteristics, kinematics of coherent structures and dynamical processes in flow evolution, have been studied systematically. A feedback model is developed to predict the self-sustained shock wave motions repeated alternately along the upper and lower surfaces of the aerofoil, which is a key issue associated with the complex flow phenomena. Based on the moving shock wave characteristics, three typical flow regimes are classified as attached boundary layer, moving shock wave/turbulent boundary layer interaction and intermittent boundary layer separation. The turbulent statistical quantities have been analysed in detail, and different behaviours are found in the three flow regimes. Some quantities, e.g. pressure-dilatation correlation and dilatational dissipation, have exhibited that the compressibility effect is enhanced because of the shock wave/boundary layer interaction. Further, the kinematics of coherent vortical structures and the dynamical processes in flow evolution are analysed. The speed of downstream-propagating pressure waves in the separated boundary layer is consistent with the convection speed of the coherent vortical structures. The multi-layer structures of the separated shear layer and the moving shock wave are reasonably captured using the instantaneous Lamb vector divergence and curl, and the underlying dynamical processes are clarified. In addition, the proper orthogonal decomposition analysis of the fluctuating pressure field illustrates that the dominated modes are associated with the moving shock waves and the separated shear layers in the trailing-edge region. The results obtained in this study provide physical insight into the understanding of the mechanisms relevant to this complex flow.

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Section: Computational Overview and Validationmentioning

confidence: 99%

Section: Validationmentioning

confidence: 99%