Hypersonic flow control using magneto-hydrodynamics

摘要

The focus of the present workison the use of magneto hydrodynamics as aflowcontrol device forsupersonic and hypersonic vehicles. A three dimensional parabolizedNavier Stokes solver was developed to take intoaccount the effects of magnetic fields,by incorporating two magneto-hydrodynamic models. The modified solver was then usedto study the effects of magneto-hydrodynamics on a variety of configurations, one studyof which involved surrogate model based optimisation procedures.The firstcomponent of researchinvolved validation of the lowmagnetic Reynoldsnumber model model against welldocumented test cases. Good agreement with the nu-merical test cases for flows past a blunt body and a flat plate boundary layer flow, both inthe presence of a magnetic field, was found. Anovel application of the method of man-ufactured solutions to the simplified mapeto-hydrodynamic model was made to ensureitsAccuracy. Assessmentof the procedures used fornumerical optimisation, were madeagainst known closed-form solutions, and a theoretical axisymmetric body of revolution.An investigation for an optimal magnetic field configuration, for an over-spedRam-jet intake was made.Itwas found that fora suitable choice of magnetic fieldstrength,shock onlipcould beachieved. Furthermore, fora suitable choice for the position ofthe magnetic fieldsource, the design condition can also be satisfied using a weaker mag-netic field. Finallya study examining the use of magnetic fields for flows past a slenderbody were was performed. Given a suitably orientated dipole source, itwas shown thatthe magnetic fieldcan introduce asymmetries,foran otherwise symmetric flowfield, andthereby introduce side formon the missile.