CFD Analysis of Dynamics of Interaction of Shock Wave -Vortex Core over Flapped Wing of Supersonic Aircraft at different angle of attack & Mach number
Mukesh Didwania1, Kamal Kishore Khatri2

1Mukesh Didwania* is currently PhD Scholar in Mechanical Engineering at Career Point University, Kota, (Rajasthan), India.
2Dr. Kamal Kishore Khatri Associate Professor, Dept. of Mechanical-Mechatronics Engineering and Lead- Centre for Material Science and Energy Studies, LNMIIT, Jaipur, (Rajasthan), India.
Manuscript received on November 22, 2019. | Revised Manuscript received on December 08, 2019. | Manuscript published on December 30, 2019. | PP: 5578-5589  | Volume-9 Issue-2, December, 2019. | Retrieval Number: B2913129219/2019©BEIESP | DOI: 10.35940/ijeat.B2913.129219
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Abstract: The objective of this paper was to analysis the condition for the appearance of the many types of interaction of a vortex core with shock wave over a flapped wing of a supersonic aircraft. A five digit NACA 23012 aero foil was selected for this work. Structured Mesh was generated by Quadrilaterals Method. Steady-state density based implicit solver and K-ω SST turbulent model was selected. Q criterion method with vorticity magnitude was used to calculate the vortex core. NACA aero foil Scaled model was manufactured by using NACA profile for experimental work and CFD results were validated by pressure coefficient calculated by wind tunnel setup. Finally, concluded that weak interaction with no vortex breakdown was observed at M= 1.4 and a strong interaction with a bubble-like vortex breakdown formed at M= 1.8 and It found that when a shock wave interact with vortex core, disturbance is generated, which expands along the shock wave and deformed into many small vortices. The flow field is compressed behind the curved shock wave which is reason of acoustic waves. This principle are related to the shock–turbulence interaction which is one of major source of noise. Also concluded that initially at low angle of attack, it observed a strong organized flow field in the downstream region which is due to less strength of the shock. The development of a transmitted shock wave across the vortex core was observed because of shock scattering phenomenon. The moderate breakdown of the vorticity field that occurs after a very strong shock at M =1.4 also observed and the breakdown was more intense when increased Mach No. up to 1.8. Weak and strong interaction region were observed and three stages of interaction found by the flow field over aerofoil at high Mach No. =1.8.
Keywords: Angle of attack, Deflection Angle, Mach No., Aero foil, Lift, Drag, Vortex, Shock wave, CFD, NACA.