Recent Assessment and Analysis of Damping Derivatives for Delta Wings in Hypersonic Flow for Curved Leading Edges with Full Sine Wave

Recent Assessment and Analysis of Damping Derivatives for Delta Wings in Hypersonic Flow for Curved Leading Edges with Full Sine Wave

Because of the pitch rate for the different amplitude of the sinus wave, flow deflection angle δ, pivot position, and the Mach numbers, this paper presents the influence of curved leading edges on the damping derivative. Results show that there is a gradual rise in the pitch damping derivatives from h = 0 with the rise in the amplitude of the maximum sine wave (i.e. positive amplitude), which decreases later in the downstream to the trailing edge before the centre of pressure is located and vice versa. There is an increase in the numerical values of the derivatives at the pressure centre position, when we consider the stability derivatives at damping for the pitch q rate. In nature, this increase is non-linear and not like the location near the leading edges. Due to the differences in the Mach numbers, flow deflection angle δ, and amplitude of the sinusoidal wave, the magnitude of the damping derivatives remained in the same range.

Author (s) Details

Renita Sharon Monis
Mathematics Department, M.I.T.E, Moodabidri, Karnataka, India, affiliated to VTU Belgaum and SMVITM, Bantakal, Karnataka, India, affliated to VTU Belgaum.

Dr. Asha Crasta
Mathematics Department, M.I.T.E, Moodabidri, Karnataka, India, affiliated to VTU Belgaum.

Sher Afghan Khan
Department of Mechanical Engineering, Faculty of Engineering, IIUM, Gombak Campus, Kuala Lumpur, Malaysia.

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