The Pressure on Flat and Anhedral Delta Wings with Attached Shock Waves

Pike, J.

doi:10.1017/s0001925900006156

Cited by 12 publications

(7 citation statements)

References 2 publications

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“…Hence light hill piston theoryor miles strong shock piston theory cannot be used but Ghosh"s piston theory will be applicable. , Where  P is free stream pressure (1) Since strips at different span wise location are assumed independent of each other, the strip can be considered as a flat plate at an angle of attack. The angle of incidence is same as that of wing.…”

Section: IImentioning

confidence: 99%

“…Angle  is the angle between the shock and the strip. A piston theory which has been used in equation (1) has been extended to supersonic flow. The expression is given below.…”

Section: IImentioning

confidence: 99%

“…The theories for steady delta wings in supersonic/hypersonic flow with shock wave attached were given by Pike [1] and Hui [2]. Carrier [3] and Hui [4] gave exact solutions for 2-D flow in the case of an oscillating wedge and for an oscillating flat plate were given by Hui [5], which is valid uniformly for all supersonic Mach numbers and wedge angles or angles of attack with attached shock wave.…”

Section: Introductionmentioning

confidence: 99%

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Effect of Angle of Attack on Stability Derivatives of a Delta Wing with Straight Leading Edge in Supersonic Flow

Crasta¹,

Khan²

2014

IOSRJM

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In the Present paper effect of angle of incidence on pitching derivatives of a delta wing with Straight 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. This combines with similitude to give a piston theory. From the results it is seen that with the increase in the Mach number, there is a decrement of stiffness as well as the damping derivatives in pitch 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 both stiffness and damping derivatives increase 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 h = 0.0, 0.2, 0.4, 0.6, 0.8, 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 both the stability derivatives were decreasing progressively with the pivot position. 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, and secondary wave reflections are neglected.

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Section: IImentioning

confidence: 99%

“…Angle  is the angle between the shock and the strip. A piston theory which has been used in equation (1) has been extended to supersonic flow. The expression is given below.…”

Section: IImentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Effect of Angle of Attack on Stability Derivatives of a Delta Wing with Straight Leading Edge in Supersonic Flow

Crasta¹,

Khan²

2014

IOSRJM

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“…The geometry of the hypersonic vehicle is taken from experimental and analytical research in the UK in the mid-1960s by Pike (1972Pike ( , 1977 and Townend (1966). The configurations in figure 11 can have the pointed nose replaced with a spatulate nose, as demonstrated by Pike.…”

Section: (B) Configuration Geometrymentioning

confidence: 99%

A demonstrator for the SSTO launcher with combined cycle propulsion

Czysz

1999

Philosophical Transactions of the Royal Society of London. Seri

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Space launch systems of the 20th century are still regarded as both costly and unsafe. They have never acquired the reliability of commercial aircraft and they cannot abort from lift-off to mid-mission without massive losses. Most types of launchers are sacrificed after launch, and both hardware and environmental costs are significant. The cost of the launcher itself dominates this operation as it is the first, last and only time it flies. The user pays for the entire vehicle. For commercial aircraft operations, the frequency of flight and the lifespan of the aircraft means that the individual passenger pays about £6 for the cost of the aircraft per flight and the remainder is for fuel and operations. For commercial space launch to become both routine and economic, the need is to achieve the reliability, the sustained operation over a long lifespan, and the easy refurbishment of commercial aircraft. In seeking this solution, design studies have accepted that the ballistic missile launch may give way to either vertical or horizontal take-off aircraft using airbreathing propulsion up to a high flight Mach number and rockets thereafter. This paper examines the factors that shape the choice of airbreathing engines and airframe characteristics for SSTO space launchers, transatmospheric vehicles, boost-glide intercontinental range vehicles, and an associated demonstrator vehicle.

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“…Malmuth (1966) obtained an analytical solution for the attached shock case at small incidence based on hypersonic small disturbance theory. Pike (1972) and Hui (1971) have analytically treated the steady delta wing in supersonic/hypersonic flow with an attached shock.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic large-deflection similitude for oscillating delta wings

Ghosh

1984

Aeronaut. j.

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A similitude has been obtained for delta wings with attached leading edge shock at large incidence in hypersonic flow. A strip theory in which flow at a spanwise location is two-dimensional has been developed. This combines with the similitude to lead to a piston theory which gives closed form solutions for unsteady derivatives in pitch and roll. The derivatives in pitch are independent of and the roll damping derivative varies linearly with the aspect ratio. Substantially the same results as the theory of Liu and Hui are obtained with remarkable computational ease.

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The Pressure on Flat and Anhedral Delta Wings with Attached Shock Waves

Cited by 12 publications

References 2 publications

Effect of Angle of Attack on Stability Derivatives of a Delta Wing with Straight Leading Edge in Supersonic Flow

Effect of Angle of Attack on Stability Derivatives of a Delta Wing with Straight Leading Edge in Supersonic Flow

A demonstrator for the SSTO launcher with combined cycle propulsion

Hypersonic large-deflection similitude for oscillating delta wings

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