Transonic Periodic Flow Subject to Adaptive Bump

Tulita, Catalin; Bénard, Emmanuel; Raghunathan, Srinivasan

doi:10.2514/6.2003-444

Cited by 3 publications

(8 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, care should be taken in experimental measurements of heat transfer effects, as surface heat transfer has been observed to introduce spurious scale effects in wind-tunnel testing (61) . Figures 12 and 13 respectively illustrate the predicted effects of cooling on transonic periodic flow on a 14% bi-convex aerofoil (21,29) and on the LV2F aerofoil (39) . For 14% bi-convex aerofoil (Fig.…”

Section: The Influence Of the Boundary-layer Transition On Periodic Mmentioning

confidence: 99%

“…In supersonic regions, the dominating effect of heat transfer is through viscosity (cooling decreases the viscosity and therefore the skin friction), whereas at subsonic speeds the dominating influence of heat transfer is through the velocity gradients (cooling increases the velocity gradients and, correspondingly, the skin friction). Cooling also has a significant effect on periodic transonic flows (21,29,39) . Heat transfer effects are related to the temperature of the wall relative to the adiabatic temperature.…”

Section: The Effect Of Heat Transfer On Periodic Motionmentioning

confidence: 99%

“…In general, some of the effects due to surface cooling on a flat plate boundary layer are analogous to that of boundary-layer suction, in that Frame 3b: The bubble extends into the wake and the shock movement is reaching its amplitude (pressure distribution) Figure 15(a). Case without bump (k = 0⋅16) (38,39) .…”

Section: The Effect Of Heat Transfer On Periodic Motionmentioning

confidence: 99%

“…Frame 3b: The is no sign of a change in the shock position on the aerofoil relative to the bump, and the lambda structure is clearly defined (pressure distribution) Figure 15(b). Case with bump (k = 0⋅24) (38,39) . Figure 15.…”

Section: Frame 1amentioning

confidence: 99%

“…A further example is the prediction of shock position for periodic flow on a 14% thick aerofoil (39) compared with the experiments of Fig. 12 is shown in Fig.…”

mentioning

confidence: 99%

See 4 more Smart Citations

Periodic transonic flow and control

et al. 2008

View full text Add to dashboard Cite

The current understanding of periodic transonic flow is reviewed briefly. The effects of boundary-layer transition, non-adiabatic wall conditions and modifications to the aerofoil surface geometry at the shock interactions on periodic transonic flow are discussed. Through the methods presented, it is proposed that the frequency of periodic motion can be predicted with reasonable accuracy, but there are limitations on the prediction of buffet boundaries associated with periodic transonic flows. Several methods have been proposed by which the periodic motion may be virtually eliminated, most relevantly by altering the position of transition fix, contouring the aerofoils surface or adding a porous surface and a cavity in the region of shock interaction. In addition, it has been shown that heat transfer can have a significant effect on buffet.

show abstract

Section: The Influence Of the Boundary-layer Transition On Periodic Mmentioning

confidence: 99%

Section: The Effect Of Heat Transfer On Periodic Motionmentioning

confidence: 99%

Section: The Effect Of Heat Transfer On Periodic Motionmentioning

confidence: 99%

Section: Frame 1amentioning

confidence: 99%

“…A further example is the prediction of shock position for periodic flow on a 14% thick aerofoil (39) compared with the experiments of Fig. 12 is shown in Fig.…”

mentioning

confidence: 99%

See 3 more Smart Citations

Periodic transonic flow and control

et al. 2008

View full text Add to dashboard Cite

show abstract

Wide domain simulations of flow over an unswept laminar wing section undergoing transonic buffet

Zauner

Sandham

2020

Phys. Rev. Fluids

View full text Add to dashboard Cite

Transonic buffet is an unsteady flow phenomenon that limits the safe flight envelope of modern aircraft. Scale-resolving simulations with span-periodic boundary conditions can provide detailed insight into the flow physics associated with buffet and can help to calibrate simplified models that are needed, for example, to develop more efficient wings based on laminar-flow supercritical sections. However, such simulations are often feasible only for severely restricted spanwise domains. In the current contribution, we analyse an unswept laminar-flow wing section (of Dassault Aviation's V2C profile) at a moderate Reynolds number of Re = 500,000 and a Mach number of M = 0.7 with spanwise domains equal to 5% and 100% of the airfoil chord. An implicit large-eddy simulation methodology, using a spectral error estimator to control the action of a high-order filter, is first validated against direct numerical simulations and then used for the domain width study. Quantitative differences, due to domain size, include an increase in amplitude and regularity of the buffet oscillations in the wider domain. Nevertheless, space-time analysis shows that key physical phenomena such as upstream-propagating shock waves are properly represented in the narrow domain and there is limited sensitivity to domain size of the aerodynamic coefficients. Even in the very wide domain, which is an order of magnitude wider than the largest turbulent structures measured at the trailing edge, certain features remain two-dimensional, including the shock and expansion waves that interact with the boundary layer upstream of transition. The transition mechanism is found to have subtle variations during a typical buffet cycle, with Kelvin-Helmholtz structures prominent during low-lift phases and oblique modes developing behind shock/boundarylayer interactions during high-lift phases. The availability of the wide-domain data is used for further study of the buffet mechanism, considering phase-averaged data and instantaneous flow fields to show the global structure of the buffet oscillation.

show abstract

Numerical Simulation of Stall Flow Control over NACA0012 Airfoil with Contour Bump

Hao

2017

55th AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

Transonic Periodic Flow Subject to Adaptive Bump

Cited by 3 publications

References 11 publications

Periodic transonic flow and control

Periodic transonic flow and control

Wide domain simulations of flow over an unswept laminar wing section undergoing transonic buffet

Numerical Simulation of Stall Flow Control over NACA0012 Airfoil with Contour Bump

Contact Info

Product

Resources

About