Date of Award

Spring 1991

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

Surendra N. Tiwari

Committee Member

Sushil K. Chaturvedi

Committee Member

Arthur C. Taylor III

Call Number for Print

Special Collections; LD4331.E56S34

Abstract

Hypersonic flows over cones and straight biconic configurations are calculated for a wide range of free stream conditions in which the gas behind the shock is treated as perfect. Effect of angle of attack and nose bluntness on these slender bodies in air is investigated extensively. The numerical procedures are based on the solution of complete Navier-Stokes equations at the nose section and parabolized Navier Stokes equations further downstream. The flow field variables and surface quantities show significant differences when the angle of attack and nose bluntness are varied. The complete flow field is thoroughly analyzed with respect to velocity, temperature, pressure and entropy profiles. The post-shock flow field is studied in detail from the contour plots of Mach number, density, pressure and temperature. Flow separation is observed on the leeward plane for an on-axis, 12.84°/ 7° (fore-cone and aft-cone angle) biconic geometry at 12° angle of attack. Also, the windward and leeward heating rates for the fore-cone section decreases by a factor of four and by a factor of five respectively, when the nose bluntness is increased by an order of magnitude. The effect of nose bluntness for slender cone persists as far as 200 nose radii downstream.

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DOI

10.25777/eykr-3v97

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