Effect of Sweep Angle on Rolling Moment Derivative of an Oscillating Supersonic/Hypersonic Delta Wing
Journal Title: International Journal of Modern Engineering Research (IJMER) - Year 2014, Vol 4, Issue 10
Abstract
In the Present paper effect of sweep angle on roll of damping derivative of a delta wing with straight leading edges for an attached shock case in supersonic/hypersonic flow has been studied analytically. A Strip theory is used in which strips at different span wise location are independent. This combines with similitude which leads to give a piston theory. The Present theory is valid for attached shock case only. The results of the present study reveals that with the increase in the sweep angle; it results in continuous decrease in the roll damping derivative, it is also seen that the magnitude of the decrement for lower sweep angle is very large as compared to the higher values of the sweep angles due to the drastic change in the plan form area. Roll damping derivative progressively increases with the angle of attack, however, with the increase in the Mach number it results in the decrement in the damping derivative and later conforms to the Mach number principle. Effects of wave reflection, leading edge bluntness, and viscosity have not been taken into account. Results have been obtained for supersonic/hypersonic flow of perfect gases over a wide range of angle of attack, plan form area, and the Mach number
Authors and Affiliations
Asha Crasta , S. A. Khan , Antony A. J
Keywords
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