Renita Sharon Monis
Research Subjects
Research Interests
Renita Sharon Monis has a total of 4 co-authors. Here are the top co-authors by number of shared publications:
- Asha Crasta
Department of Mathematics, M.I.T.E, Moodabidri & Affiliated To VTU, Belgavi, Karnataka, India
1 shared publication - Erwin Sulaeman
Department of Mechanical and Aerospace Engineering, College of Engineering, United Arab Emirates University, Al-Ain P.O. Box 15551, United Arab Emirates
1 shared publication - Parvathy Rajendran
Department of Mechanical and Aerospace Engineering, United Arab Emirates University, Al Ain, United Arab Emirates
1 shared publication - Sher Afghan Khan
Department of Mechanical and Aerospace Engineering, Faculty of Engineering, International Islamic University, Kuala Lumpur, Malaysia
1 shared publication
Latest Publications
- Open Access
- 5 March 2022
- Published by Akademia Baru Publishing in Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
- Vol. 92 (1) , 1-8
Comparative Study of Quasi Steady and Unsteady Damping Derivatives for Delta Wings in Hypersonic Flow for Half Sine Wave
Correlation investigation of quasi-steady and unsteady damping derivatives of delta wing is analyzed and contemplated, with leading edges bent in the current paper. The current paper realizes that the quasi-steady damping derivative considers only the rate of pitch, not the rate of the angle of attack. In contrast, unsteady damping derivatives account for pitch rate and the rate of the angle of attack. Results show a reformist reduction in the damping derivatives as the Mach number increases in quasi-steady and unsteady cases. Outcomes are computed for a varied range of Mach Numbers and deflection angles due to the pitch rate of different amplitudes of half-sine waves. The outcomes for the damping derivative for a fixed pivot position show different behaviour for different values of the flow deflection angles observed here. As in straight leading edge, even in the curved leading edge, steady-state is attained earlier in quasi-steady than unsteady.
- 5 March 2022
- Published by Akademia Baru Publishing in Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
- Vol. 92 (1) , 1-8
Open AccessComparative Study of Quasi Steady and Unsteady Damping Derivatives for Delta Wings in Hypersonic Flow for Half Sine Wave
Correlation investigation of quasi-steady and unsteady damping derivatives of delta wing is analyzed and contemplated, with leading edges bent in the current paper. The current paper realizes that the quasi-steady damping derivative considers only the rate of pitch, not the rate of the angle of attack. In contrast, unsteady damping derivatives account for pitch rate and the rate of the angle of attack. Results show a reformist reduction in the damping derivatives as the Mach number increases in quasi-steady and unsteady cases. Outcomes are computed for a varied range of Mach Numbers and deflection angles due to the pitch rate of different amplitudes of half-sine waves. The outcomes for the damping derivative for a fixed pivot position show different behaviour for different values of the flow deflection angles observed here. As in straight leading edge, even in the curved leading edge, steady-state is attained earlier in quasi-steady than unsteady.