Supersonic Similitude for Oscillating Nonplanar Wedge

Crasta, Asha; Khan, Sher Afghan

doi:10.9790/5728-10261524

Cited by 12 publications

(9 citation statements)

References 11 publications

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“…5 and with an attached bow shock. The extension of Ghosh's work on pitching non-planar wedges was developed by Crasta and Khan to evaluate the aerodynamic stability derivatives in pitch for both Supersonic [2] and Hypersonic flows [10] to [12].…”

Section: Aysha Shabana Renita Sharon Monis Asha Crasta and S A Khanmentioning

confidence: 99%

The Computation of Stiffness Derivative for an Ogive in the Hypersonic Flow

Shabana¹,

Tjprc²

2018

IJMPERD

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Expression for Stiffness derivative for an Ogive is derived with the suppositions of the arc on the nose of the cone from the air is being considered as perfect gas and the viscosity being neglected, the motion is quasi-steady, and the nose deflection angle of the Ogive θ is in such a way that the M 2 after the shock is > 2.5. It is seen that due to the increment in angle θ, the stiffness derivative increases linearly due the progressive increase in the plan form area of the nose shape. The results indicate that there is a 38 percent increase in the stability derivative when the flow deflection θ was enhanced in the range of 5 to 10 degrees. With the further enhancement in the flow deflection angle θ from ten degrees and above, does not yield substantial increase in the stability derivative. Due to this change in the surface pressure distribution will lead to shift the location of centre of pressure, from the hinged position h = 0.5 to 0.8. The centre of pressure also has shifted towards the downstream, which lies in the range from h = 0.72 to 0.85.

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Section: Aysha Shabana Renita Sharon Monis Asha Crasta and S A Khanmentioning

confidence: 99%

The Computation of Stiffness Derivative for an Ogive in the Hypersonic Flow

Shabana¹,

Tjprc²

2018

IJMPERD

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“…The stability derivatives have been obtained for sharp wedges formed by two flat plates. Crasta &Khan [7][8][9][10] have given a theory for the quasi steady flow for the wedge which is an extension of Ghosh's theory, which predicts the stability derivatives in pitch and roll. A similitude implemented for hypersonic flow with planar wedge by attaching bow shock at high incidence.…”

Section: Introductionmentioning

confidence: 99%

Effect of Inertia Level on Aerodynamic Derivatives of a wedge in Hypersonic Flow

Pavitra¹,

Lavanya²,

Khan³

2016

IOSR

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In this paper a 2-dimensional slender bodies in hypersonic flow at high angle of attack with different Mach number has been implemented. By utilizing the concept of a piston moving in a cylinder at any speed, relations for stability derivatives are obtained for a wedge, which depends on the flight Mach number and semi vertex angle of the wedge. Stiffness derivatives decreases linearly with the increase in the Mach number for h = 0, 0.2, 0.4 but for Mach number 10 and above the steady state is achieved and stability derivative becomes independent of Mach number. For pivot positions h = 0.6, 0.8, and 1.0 unlike for h = 0 to 0.4 the stability derivative increases up to Mach 10 and again it becomes independent of Mach number. The variation of the damping derivatives is unaltered for all the values of the pivot positions. The damping derivative decreases marginally and then it becomes independent of Mach number. Viscous effects, secondary wave reflections are neglected in the present study. In the present study the real gas effects and leading edge bluntness have not been taken into considerations.

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“…The effect of viscosity and secondary wave reflection has not been included. Crasta and Khan have studied the hypersonic and supersonic similitude for planar wedge ( [17], [12]), for Delta wing ( [11], [13]) and for Delta wing with curved leading edges ( [14], [16]). Crasta and Khan have further extended the similitude to study the stability derivatives for Newtonian limit for planar wedge [19], delta wing [18] and delta wing with curved leading edges [15].…”

Section: Introductionmentioning

confidence: 99%