Title :
Effect of angle of incidence on stability derivatives of a wing
Author :
Crasta, Asha ; Khan, Shoab Ahmed
Author_Institution :
Dept. of Math., Jain Univ., Bangalore, India
Abstract :
In the Present paper effect of angle of incidence on pitching derivatives of a delta wing with curved leading edges of a attached shock case is been studied. A Strip theory is used in which strips at different span wise location are independent. This combines with similitude to give a piston theory. From the results it is found that stiffness and damping derivatives in pitch increasing linearly up to angle of attack 250 and then non-linearity creeps in. The Present theory is valid only for attached shock case. Effects of wave reflection and viscosity have not been taken into account. Results have been obtained for hypersonic flow of perfect gases over a wide range of angle of attack and Mach number.
Keywords :
Mach number; aerospace components; damping; hypersonic flow; mechanical stability; shock waves; viscosity; Mach number; damping derivative; delta wing; hypersonic flow; incidence angle; nonlinearity creeps; perfect gases; piston theory; pitching derivatives; shock case; stability derivatives; stiffness derivative; strip theory; viscosity; wave reflection; Angle of incidence; Attached shock wave; Curved leading edges; Hypersonic; Pitching derivatives; delta wings;
Conference_Titel :
Research & Technology in the Coming Decades (CRT 2013), National Conference on Challenges in
Conference_Location :
Ujire
Electronic_ISBN :
978-1-84919-868-4
DOI :
10.1049/cp.2013.2523
