Hypersonic large-deflection similitude for oscillating delta wings

Ghosh, Kunal

doi:10.1017/s0001924000020868

Cited by 20 publications

(7 citation statements)

References 17 publications

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“…The expression for pressure ratio at the nose of the cone in the case of bow-attached shock obtained by Ghosh [11] is given in Eq. (1).…”

Section: Fig 1 Geometry Of Conementioning

confidence: 99%

“…In the case of an oscillating cone, Ghosh [11] is adopted the equilibrium surface of the cone is perpendicular to the similitude slab at a distance x 1 from the apex. The boat tail helmets can reduce drag studied by Pathan et al, [21] and found that the aerodynamic drag reduces when the helmet shape is streamlined.…”

Section: Fig 1 Geometry Of Conementioning

confidence: 99%

“…It includes Light Hill's [8] piston theory and Mile's Shock expansion theory [10]. Ghosh [11] has applied this concept of order of Ø 2 where Ø is the angle between the plane approximating the windward surface and the attached shock wave. Ghosh [11] obtained the similitude for oscillating delta wings for attached shock waves at hypersonic Mach number with a high angle of incidence.…”

Section: Introductionmentioning

confidence: 99%

“…Ghosh [11] has applied this concept of order of Ø 2 where Ø is the angle between the plane approximating the windward surface and the attached shock wave. Ghosh [11] obtained the similitude for oscillating delta wings for attached shock waves at hypersonic Mach number with a high angle of incidence. The variation in surface pressure distribution at the large angle of incidence and high Mach numbers in the case of curved leading edge for the delta wing was studied by Crasta et al, [12].…”

Section: Introductionmentioning

confidence: 99%

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Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Shaikh

Pathan²,

Kumar

et al. 2023

ARFMTS

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In the present study, the prime attention is to numerically simulate the surface pressure distribution over the slant length of the cone at the various Mach numbers and for the considerable range of semi-cone angles. The Computational Fluid Dynamics (CFD) analysis is used to simulate the surface pressure distribution numerically. The hypersonic Mach numbers, semi-cone angle, and various locations along the slant length of a cone are considered parameters for this research work. The Mach numbers (M) considered for the research work are 5, 7, 9, 11, 13, and 15. The cone angle (θ) from 5° to 25° is considered. The results of pressure (P/Pa) are recorded at various locations (x/L) along the slant length of the cone as 0.1 to 1. The pressure distribution results are obtained by CFD analysis and compared with the analytical results available in the literature for Mach number 5. The findings obtained by CFD analysis and analytical results show good agreement. In this investigation, it is observed that the Mach number, cone angle, and slant length of the cone are the highly influential parameters for the surface pressure distribution. The pressure distribution over the slant length of the cone increases with an increase in the Mach number and the semi-cone angle.

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“…The expression for pressure ratio at the nose of the cone in the case of bow-attached shock obtained by Ghosh [11] is given in Eq. (1).…”

Section: Fig 1 Geometry Of Conementioning

confidence: 99%

Section: Fig 1 Geometry Of Conementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Shaikh

Pathan²,

Kumar

et al. 2023

ARFMTS

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“…The relationship between Lighthill [1] & Mile's, and Ghosh & Mistry's [5] piston theory for the order of two If the shock wave is attached, the angle between the plane and the shock generally relates to the windward surface [3][4]. Ghosh & Mistry [5] has discovered a similitude in hypersonic flow for delta wings with an associated leading edge shock at significant incidence [6]. Hui [3] studied, generated the exact solution in an oscillating wedge for a 2D flow, and obtained the solutions for all supersonic Mach numbers and angle of attack while taking into account the linked shock wave for an oscillating flat plate.…”

Section: Introductionmentioning

confidence: 99%

Analytical and Numerical Simulation of Surface Pressure of an Oscillating Wedge at Hypersonic Mach Numbers and Application of Taguchi's Method

Shamitha

Crasta²,

Pathan³

et al. 2023

ARASET

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This paper aims to estimate the surface pressure of a wedge at hypersonic Mach numbers at a considerable angle of incidence. The Ghosh similitude, corresponding strip theory, and piston theory are used to determine the pressure distribution analytically, and the results are compared to those of the CFD analysis. The theory is valid when the shock wave is attached to the leading edge of the nose of the wedge. Pressure on the windward surface was considered in the analysis. The pressure on the Lee surface is neglected. The condition for the validity of the theory is that the Mach number M2 behind the shock wave is greater than 2.5. The parameters taken into account for the study are the wedge angle and Mach number. The range of wedge angle considered is from 5 to 25 degrees and the Mach number considered is from 5 to 15. The analytical and the CFD results are in good agreement. The findings indicate that the parameters like wedge angle and Mach number are influential parameters that influence the wedge surface static pressure. The surface static pressure rises with an increase in Mach number and wedge angle.

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Hypersonic flow past non-slender wedges, cones and ogives in oscillation

1985

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SummaryGhosh’s large-deflection hypersonic similitude and consequent plane and conico-annular piston theories have been applied to obtain unsteady pressure and the pitching moment derivatives for oscillating non-slender wedges, cones and ogives. The plane piston theory for a wedge is extended from a quasi-steady analysis, which gives the moment derivative due to pitch rate Cmq, to an unsteady analysis; the two analyses combine to give the moment derivative due to incidence rate , which is shown here to be the same for wedges and quasi-wedges. The present theory can separately give Cmq and for a quasiwedge of arbitrary shape; this principle is illustrated for a particular quasi-wedge namely the parabolic arc plane ogive. In comparison, a previous theory by Hui gave only the sum of Cmq and , only for wedges. The conico-annular piston theory is employed to obtain Cmθ, which is the moment derivative due to a steady pitch angle, and Cmq for non-slender cones and axisymmetric ogives in closed form for the first time.

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Hypersonic large-deflection similitude for oscillating delta wings

Cited by 20 publications

References 17 publications

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Analytical and Numerical Simulation of Surface Pressure of an Oscillating Wedge at Hypersonic Mach Numbers and Application of Taguchi's Method

Hypersonic flow past non-slender wedges, cones and ogives in oscillation

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