Aeroptical effects caused by supersonic airflow around an ogival body

2018 ◽  
Keyword(s):  
Supersonic Airflow ◽  
Ogival Body

PROBLEM OF INTERFERENCE OF AN OGIVAL BODY OF REVOLUTION WITH THE WIND-TUNNEL STING AND SPECIFIC FEATURES OF COMPUTING THIS PROBLEM

2011 ◽  
Vol 42 (3) ◽  
pp. 321-344 ◽  
Author(s):  
Sergey Mikhailovich Bosnyakov ◽  
Vladimir Viktorovich Vlasenko ◽  
Innokentii Aleksandrovich Kursakov ◽  
Sergey Vladimirovich Mikhaylov ◽  
Jurgen Quest
Keyword(s):  
Wind Tunnel ◽  
Body Of Revolution ◽  
Ogival Body

scholarly journals A Combined Energy Method for Flutter Instability Analysis of Weakly Damped Panels in Supersonic Airflow

Mathematics ◽  
2021 ◽  
Vol 9 (10) ◽  
pp. 1090
Author(s):  
Xiaochen Wang ◽  
Zhichun Yang ◽  
Guiwei Zhang ◽  
Xinwei Xu
Keyword(s):  
Energy Balance ◽  
Energy Method ◽  
Plate Theory ◽  
Dynamic Pressure ◽  
Physical Nature ◽  
Aeroelastic System ◽  
Dissipation Energy ◽  
Supersonic Airflow ◽  
Flutter Instability ◽  
Modal Damping

A combined energy method is proposed to investigate the flutter instability characteristics of weakly damped panels in the supersonic airflow. Based on the small damping assumption, the motion governing partial differential equation (PDE) of the panel aeroelastic system, is built by adopting the first-order piston theory and von Karman large deflection plate theory. Then by applying the Galerkin procedure, the PDE is discretized into a set of coupled ordinary differential equations, and the system reduced order model (ROM) with two degrees of freedom is obtained. Considering that the panel aeroelastic system is non-conservative in the physical nature, and assuming that the panel exhibits a single period oscillation on the flutter occurrence, the non-conservative energy balance principle is applied to the linearized ROM within one single oscillation period. The obtained result shows that the ROM modal coordinate amplitudes ratio is regulated by the modal damping coefficients ratio, though each modal damping coefficient is small. Furthermore, as the total damping dissipation energy can be eliminated due to its smallness, the He’s energy balance method is applied to the undamped ROM, therefore the critical non-dimensional dynamic pressure on the flutter instability occurrence, and the oscillation circular frequency amplitude relationship (linear and nonlinear form) are derived. In addition, the damping destabilization paradoxical influence on the system flutter instability is investigated. The accuracy and efficiency of the proposed method are validated by comparing the results with that obtained by using Routh Hurwitz criteria.

scholarly journals CFD modeling of supersonic airflow generated by 2D nozzle with and without an obstacle at the exit section

2015 ◽  
Vol 43 (2) ◽  
pp. 107-113 ◽  
Author(s):  
Olivera Kostic ◽  
Zoran Stefanovic ◽  
Ivan Kostic
Keyword(s):  
Cfd Modeling ◽  
Exit Section ◽  
Supersonic Airflow

scholarly journals Microwave discharge initiated by double laser spark in a supersonic airflow – CORRIGENDUM

2015 ◽  
Vol 81 (3) ◽  
Author(s):  
R. S. Khoronzhuk ◽  
A. G. Karpenko ◽  
V. A. Lashkov ◽  
D. P. Potapeko ◽  
I. Ch. Mashek
Keyword(s):  
Microwave Discharge ◽  
Supersonic Airflow ◽  
Laser Spark ◽  
Made In

There was an error made in the name of the author in the above published article. The fourth author's name should have appeared as ‘D. P. Potapenko’. This error has now been rectified in the original article.

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