Two-dimensional Supersonic Thrust Vectoring Using Staggered Ramps

[+] Author and Article Information
Carlos F. Montes

M.S. Mechanical and Aerospace Engineering, Department of Mechanical and Aerospace Engineering, UC Davis 3401 Hillsborough Drive, APT 9, Concord, CA 94520

Roger L. Davis

Professor, Department of Mechanical and Aerospace Engineering, UC Davis One Shields Ave., 2132 Bainer Hall, Davis, CA 95616

1Corresponding author.

ASME doi:10.1115/1.4035848 History: Received October 07, 2016; Revised December 29, 2016


The thrust vectoring performance of a novel nozzle mechanism was numerically investigated. The nozzle was designed for supersonic, air-breathing engines using published engine data, isentropic relationships, and piecewise quartic splines. The mechanism utilizes two staggered, adjustable ramps. A baseline inviscid numerical simulation without ramps verified the nozzle design by comparing the results to analytical data. Nine ramp configurations were analyzed under steady-state turbulent viscous conditions, using two sets of inlet parameters corresponding to inlet conditions with and without an afterburner. The realizable k-e model was used to model the turbulence field. Area-weighted integrals of the exit flow showed superior flow deflection with the non-afterburning inlet flow parameters. Calculations of the mean flow deflection angles showed that the flow can be deflected as much as 30° in a given direction with the largest ramp length and angle values. The smallest ramp length (less than 5% of the nozzle length) demonstrated as much as 21° in flow deflection.

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