ISSN Online: 2688-7231
ISBN Online: 978-1-56700-524-0
Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India
Numerical Investigation of Energy Deposition based Drag Reduction Technique for Reacting Flows
The field of supersonic/hypersonic aerodynamics is centered on shock waves and their interactions that alter the flow fields which cause excessive wave drag forces as well as heat loads on bodies under consideration. Therefore, separate in-house finite volume based inviscid and multi species reacting gas flow unstructured solvers are implemented for Earth and Mars atmospheres to investigate the steady energy deposition based drag reduction technique. Present studies are carried out by depositing energy at various locations upstream of two different configurations of 15° half angle truncated cone-cylinder of base radius of 15 mm flowing at Mach 5. It has been found that deposited energy offers more reduction in drag with increment in location of energy spot up to a certain range then it starts to decrease but reduction is still prevailing. At the higher freestream stagnation enthalpy cases, it has been found that conical shock gets delayed and pushed inward direction which leads to reduction in drag reduction efficiency. Moreover, studies show that relative drag reduction in case of Mars atmosphere is lesser than that of Earth for same freestream conditions.