Effect of Mach number on Stiffness and Damping Derivatives for Oscillating Hyersonic Non-Planar Wedge

Crasta, Asha; Khan, Sher Afghan

doi:10.9790/1684-11280411

Cited by 8 publications

(6 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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“…Ghosh [13] has obtained a similitude and two similarity parameters for shock attached oscillating delta wings at large incidence. Crasta and Khan have extended the Ghosh similitude to Hypersonic/supersonic flows past a planar wedge [14] and [18] and Non planar wedge [20], [21], and [22]. Crasta and Khan have obtained stability derivatives in pitch and roll of a delta wing with straight leading edge [23] and [24] and curved leading edges for supersonic flows [15] and Hypersonic flows [16].…”

Section: Introductionmentioning

confidence: 99%

Effect of Angle Of Attack on Stiffness Derivative of an Oscillating Supersonic Delta Wing with Curved Leading Edges

Crasta¹,

Khan²

2014

IOSRJMCE

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In the Present paper effect of angle of incidence on Stiffness derivative of a delta wing with Curved leading edges for attached shock case in Supersonic Flow has been studied. A Strip theory is used in which strips at different span wise location are independent of each other. This combines with similitude to give a piston theory which gives closed form solutions for stiffness derivatives at low supersonic to high supersonic Mach numbers. From the results it is seen that with the increase in the Mach number, there is a continuous decrease in the magnitude of stiffness derivatives for all the Mach number tested, however, the magnitude of decrement for different inertia level will differ. It is seen that with the increase in the angle of attack the stiffness derivative increases linearly, nevertheless, this linear behavior limit themselves for different Mach numbers. For Mach number M = 2, this limiting value of validity is fifteen degrees, for Mach 2.5 & 3, it is twenty five degrees, whereas, for Mach 3.5 & 4 it becomes thirty five degrees, when these stability derivatives were considered at various pivot positions; namely at h = 0.0, 0.4, 0.6, and 1.0. After scanning the results it was observed that with the shift of the pivot position from the leading edge to the trailing edge, the magnitude of stiffness and the damping derivatives continue to decrease progressively. Results have been obtained for supersonic flow of perfect gases over a wide range of angle of attack and Mach number. The effect of real gas, leading edge bluntness of the wing, shock motion, and secondary wave reflections are neglected.

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Effect of Mach number on Stiffness and Damping Derivatives for Oscillating Hyersonic Non-Planar Wedge

Cited by 8 publications

References 11 publications

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

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

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

Effect of Angle Of Attack on Stiffness Derivative of an Oscillating Supersonic Delta Wing with Curved Leading Edges

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