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

Abstract

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.

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

“…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]. Musavir et al, [13] studied the computational and analytical investigation of aerodynamic derivatives for the oscillating wedge.…”

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

“…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]. Crasta and Khan have studied the effect of angle of incidence on pitching derivatives and roll of a damping derivative of a delta wing with curved leading edges for an attached shock case [17] and [27].…”

Supersonic Similitude for Oscillating Nonplanar Wedge

“…Ghosh's piston theory has been applied to non-planar cases, both steady and unsteady. 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 tostudy the stability derivatives for Newtonian limit for planar wedge, delta wing [18] and delta wing with curved leading edges [15].…”