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Abstract

A transient finite-difference method was developed to compute the transonic flow about blunt lipped ducted bodies in supersonic free streams. Moretti's second order accurate and explicit method was adapted for the computation of the interior regions and a transient
method, characteristics was used at the boundaries. The flow velocity at the internal boundary of the ducted body was subsonic or supersonic as required. For the subsonic internal boundary case, the internal boundary was specially treated so as to enable the mass flow ratio and/ or the axial velocity component to be prescribed. Results were presented for the Mach number range 1.82 ≤ M ≤ 3.0.

Three inlet shapes were investigated for axisymmetric and two-dimensional flows: two circular section inlets and a symmetric elliptic section. The external drag, cowl drag, additive drag and total pressure recovery were also calculated.

Computer Programs were written in FORTRAN for use on CDC 6600 and cDc 7600 digital computers.

Publication Type:	Thesis (Doctoral)
Subjects:	Q Science > QA Mathematics > QA75 Electronic computers. Computer science T Technology > T Technology (General) T Technology > TL Motor vehicles. Aeronautics. Astronautics
Departments:	School of Science & Technology > Department of Engineering School of Science & Technology > School of Science & Technology Doctoral Theses Doctoral Theses

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