The influence of acceleration and deceleration on shock wave movement on and around aerofoils in transonic flight

Roohani, H.; Skews, B. W.

doi:10.1007/s00193-009-0207-9

Cited by 9 publications

(12 citation statements)

References 4 publications

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“…Significant effects on aerofoil lift and drag were observed [44] in the subsonic range, and we deduce that ~0.1 may be a reasonable indicator in this range. In the high velocity ranges is lower, but shock wave effects dominate flow history in this range, as described under section 2, the Mach number M ~ 1.…”

Section: 1mentioning

confidence: 68%

“…It was then demonstrated that drag on an axisymmetric flare missile dropped by 20% in comparison with steady values if the flare geometry was accelerated through the transonic range at 4 500 ms -1 . Roohani and Skews have conducted detailed studies of the unsteady aerodynamics of accelerating bodies, such as aerofoils [40][41][42][43][44] and axisymmetric objects [45] undergoing unidirectional acceleration through the subsonic and transonic ranges. This was modelled numerically using source terms added to the momentum and energy equations in the code FLUENT [46].Shock wave boundary layer interaction was found to have significant effect on the shock wave position and strength in the transonic range.…”

Section: Earlier Workmentioning

confidence: 99%

“…Linear acceleration The works of Roohani and Skews [41,43,44] focus on acceleration and deceleration effects when the acceleration is parallel to the velocity of the object. In this case, the conservation equations in the relative frame Σ′ are as follows, given that = 0, and therefore = .…”

Section: 1mentioning

confidence: 99%

“…Parameters for their cases are shown in Table 1 Table 1 Typical parameters for aerofoils and air-to-air missiles. Data for aerofoils is from Roohani and Skews [44].…”

Section: 1mentioning

confidence: 99%

“…This obviously important parameter determines whether wake effects and shocks propagate faster than the aerofoil itself. In this case, ̈⁄ < 0, shocks may overtake an aerofoil [44], and stand-off bow shocks may exist at subsonic body velocities [44,52]. For transonic acceleration or ̈⁄ > 0, shocks on convex surfaces are likely to be found forward of the steady state position [44].…”

Section: 1mentioning

confidence: 99%

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Theoretical treatment of fluid flow for accelerating bodies

Gledhill¹,

Roohani

Forsberg

et al. 2016

Theor. Comput. Fluid Dyn.

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Most computational fluid dynamics simulations are, at present, performed in a body-fixed frame, for aeronautical purposes. With the advent of sharp manoeuvre, which may lead to transient effects originating in the acceleration of the centre of mass, there is a need to have a consistent formulation of the Navier–Stokes equations in an arbitrarily moving frame. These expressions should be in a form that allows terms to be transformed between non-inertial and inertial frames and includes gravity, viscous terms, and linear and angular acceleration. Since no effects of body acceleration appear in the inertial frame Navier–Stokes equations themselves, but only in their boundary conditions, it is useful to investigate acceleration source terms in the non-inertial frame. In this paper, a derivation of the energy equation is provided in addition to the continuity and momentum equations previously published. Relevant dimensionless constants are derived which can be used to obtain an indication of the relative significance of acceleration effects. The necessity for using computational fluid dynamics to capture nonlinear effects remains, and various implementation schemes for accelerating bodies are discussed. This theoretical treatment is intended to provide a foundation for interpretation of aerodynamic effects observed in manoeuvre, particularly for accelerating missiles.

Funding agencies: DRDB [KT466921, KT528944, KT470887]

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Section: 1mentioning

confidence: 68%

Section: Earlier Workmentioning

confidence: 99%

Section: 1mentioning

confidence: 99%

“…Parameters for their cases are shown in Table 1 Table 1 Typical parameters for aerofoils and air-to-air missiles. Data for aerofoils is from Roohani and Skews [44].…”

Section: 1mentioning

confidence: 99%