Ship-helo coupled airwake aerodynamics: A comprehensive review

Shukla, Shrish; Sinha, Sawan Suman; Singh, Sadhna

doi:10.1016/j.paerosci.2019.02.002

Cited by 39 publications

(17 citation statements)

References 50 publications

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“…A significant number of papers dealing with computational studies on different physical and numerical aspects of ship-helo DI are gathered during extensive literature survey. 34 These reported studies have highlighted that the RANS-based turbulence models are the most preferred due to its suitability and wide range of applications and hence makes it more robust for parametric computation of such complex DI turbulent flows among other computational methods. However, these models are not universally accepted and hence have to be validated against the experimental database for better accuracy and reliability.…”

Section: Computational Methodologymentioning

confidence: 99%

“…The boundary conditions selected are based on the literature survey. 34 A pressure-based solver is used along with incompressible steady air flow consideration under atmospheric pressure field. The turbulence specifications namely turbulent intensity and length scale are considered based on the literature.…”

Section: Plan Of Studymentioning

confidence: 99%

“…The turbulence specifications namely turbulent intensity and length scale are considered based on the literature. 34,35 The following boundary conditions are prescribed (Figure 8): The wall boundary condition with no-slip for all the three velocity components is applied at far-field of computational domain, as the wind tunnel experiments are being modelled. Similarly, the ship and helicopter fuselage geometry are assigned wall with no-slip condition. The computational domain is divided into two fluid zones: (i) ship and (ii) SRD. They share a common boundary at SRD exit.…”

Section: Plan Of Studymentioning

confidence: 99%

“…The turbulence specifications namely turbulent intensity and length scale are considered based on the literature. 34,35 The following boundary conditions are prescribed (Figure 8):…”

Section: Computational Domain Grids and Boundary Conditionsmentioning

confidence: 99%

“…During our literature review, 34 we observed that there is an absence of design criteria in open domain to grade a particular combination of ship and helicopter DI for ensuring minimum standards of safe helo operations for naval ship. However, the widely scattered and limited literature in this field reveals that for any ship-helicopter combination, the pilot workload, thrust and pedal margins are the three main contributors which define the operational limitations.…”

Section: Quantities Of Interestmentioning

confidence: 99%

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A conceptual method to assess ship-helicopter dynamic interface

Shukla

Singh

Sinha

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The combined operation of a ship and a helicopter is ubiquitous in every naval organization. The operation of a ship in combination with the landing and take-off operations of a helicopter results in a very complex flow phenomenon. This is due to the presence of ship airwakes, strong velocity gradients and widely varying turbulence length scales. An accurate assessment of the resultant flow phenomena is an outstanding challenge for naval architects as well as researchers. A conceptual method to gain insight into the combined ship-helo flow phenomena over a helodeck is presented. The prime objective of this work is to develop an economical design tool employing both experimental as well as computational techniques to simulate the ship-helicopter coupled environment regime at early design stages reasonably well so as to ease the burden of expensive and risky sea trials. For this purpose, a simplified dynamic interface (SDI) model is proposed to investigate the coupled effects of ship airwake and helicopter rotor downwash. The paper reports a parametric analysis to study the coupled ship-helo airwake behaviour and its impact on helicopter fuselage over the ship helodeck for different ship speed regimes by the proposed SDI model. Further, an attempt has been made to set up preliminary design criteria to grade the ship-helicopter interface for ensuring minimum standards of safe helo operations. Finally, we discuss the impact of the coupled flow dynamics in terms of induced fuselage drag, cross-flow characteristics, rotor plane wake and velocity gradients existing over the helodeck region and evaluate the proposed design criteria.

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Section: Computational Methodologymentioning

confidence: 99%

Section: Plan Of Studymentioning

confidence: 99%

Section: Plan Of Studymentioning

confidence: 99%

“…The turbulence specifications namely turbulent intensity and length scale are considered based on the literature. 34,35 The following boundary conditions are prescribed (Figure 8):…”

Section: Computational Domain Grids and Boundary Conditionsmentioning

confidence: 99%

Section: Quantities Of Interestmentioning

confidence: 99%

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A conceptual method to assess ship-helicopter dynamic interface

Shukla

Singh

Sinha

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aerodynamics of smooth and rough square-section prisms at incidence in very high Reynolds-number cross-flows

Hinsberg

2021

Exp Fluids

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The aerodynamics of smooth and slightly rough prisms with square cross-sections and sharp edges is investigated through wind tunnel experiments. Mean and fluctuating forces, the mean pitch moment, Strouhal numbers, the mean surface pressures and the mean wake profiles in the mid-span cross-section of the prism are recorded simultaneously for Reynolds numbers between 1$$\times$$ × 10$$^{5}$$ 5 $$\le$$ ≤ Re$$_{D}$$ D $$\le$$ ≤ 1$$\times$$ × 10$$^{7}$$ 7 . For the smooth prism with $$k_s$$ k s /D = 4$$\times$$ × 10$$^{-5}$$ - 5 , tests were performed at three angles of incidence, i.e. $$\alpha$$ α = 0$$^{\circ }$$ ∘ , −22.5$$^{\circ }$$ ∘ and −45$$^{\circ }$$ ∘ , whereas only both “symmetric” angles were studied for its slightly rough counterpart with $$k_s$$ k s /D = 1$$\times$$ × 10$$^{-3}$$ - 3 . First-time experimental proof is given that, within the accuracy of the data, no significant variation with Reynolds number occurs for all mean and fluctuating aerodynamic coefficients of smooth square prisms up to Reynolds numbers as high as $$\mathcal {O}$$ O (10$$^{7}$$ 7 ). This Reynolds-number independent behaviour applies to the Strouhal number and the wake profile as well. In contrast to what is known from square prisms with rounded edges and circular cylinders, an increase in surface roughness height by a factor 25 on the current sharp-edged square prism does not lead to any notable effects on the surface boundary layer and thus on the prism’s aerodynamics. For both prisms, distinct changes in the aerostatics between the various angles of incidence are seen to take place though. Graphic abstract

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A continuously scanning spatiotemporal averaging method for obtaining volumetric mean flow measurements with stereoscopic PIV

Zigunov¹,

Seckin²,

Huss³

et al. 2023

Exp Fluids

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In this study, a variation of the stacked stereoscopic PIV technique is proposed to perform fully volumetric (3-dimensions, 3-components) measurements of average flow fields within a single experiment through the usage of an automated traversing system that continuously scans the SPIV light sheet over a linear path. The simultaneous measurement of the traverse location and the laser Q-switch pulse enables the automated assignment of instantaneous PIV fields to known physical coordinates, enabling spatiotemporal averaging in postprocessing to obtain volumetric measurements of a flow field. This method provides a trade-off between spatial resolution of the volume measurements and statistical convergence of the spatiotemporal averages, enabling volumetric measurements under challenging experimental conditions where only stereoscopic PIV is viable.A comparison with the more traditional temporal averaging method and planar PIV are presented to demonstrate the capabilities and limitations of this technique in realistic, challenging experimental setups. It is found that the spatiotemporal averaging convergence behavior differs slightly from the traditional temporal averaging for the wake of a bluff body model, however relative errors lower than two standard deviations can still be attained. Thus, this technique presents a viable alternative for rapid 3D reconstruction of averaged flow fields that can provide invaluable insight of various flow topologies.

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Ship-helo coupled airwake aerodynamics: A comprehensive review

Cited by 39 publications

References 50 publications

A conceptual method to assess ship-helicopter dynamic interface

A conceptual method to assess ship-helicopter dynamic interface

Aerodynamics of smooth and rough square-section prisms at incidence in very high Reynolds-number cross-flows

A continuously scanning spatiotemporal averaging method for obtaining volumetric mean flow measurements with stereoscopic PIV

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