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Design optimization of truncated aero spike nozzle with convex tip for thrust escalation using expansion waves

Baskaran, RV and Harisrinivasan, U and Sanal Kumar, VR (2018) Design optimization of truncated aero spike nozzle with convex tip for thrust escalation using expansion waves. In: 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018, 9 - 11 July 2018, Cincinnati, Ohio.

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Official URL: https://doi.org/10.2514/6.2018-4861


In this paper 2D numerical studies have been carried out using a validated density based, SST k-ω turbulence model for the design optimization of a conventional aero spike nozzle facilitated with a convex-tip at the truncated region in order to generate expansion waves for the thrust escalation lucratively. In this numerical study a complete implicit finite volume scheme of the compressible, Navier-Stokes equations is employed. As a part of the code validation and calibration the numerically predicted boundary layer blockage at the Sanal flow choking conditions for a channel flow is verified with the closed form analytical model of V.R. Sanal Kumar et al. [1] (AIP Advances, 8, 025315, 2018) and found excellent agreement with the exact solution. We observed through parametric studies that the expansion waves generated through the convex-tip having 10° expansion angle could escalate the overall thrust on the order of 15.87 % at the sea level. Note that the convex tip facilitated at 40 % truncation location shows higher momentum thrust than the traditional spike nozzle and it is corroborated with the existing literature. We concluded that the aero spike nozzle with backward facing ramp, at an angle of 10° from the spike surface where 40 % truncation location prevails, ensures a substantial thrust escalation at the sea level due to the generation of expansion waves. This paper is a pointer towards for the 3D geometry optimization of truncated aero spike nozzle with convex step tip surface for lucrative industrial applications.

Item Type: Conference Paper
Publication: 2018 Joint Propulsion Conference
Publisher: American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information: The copyright for this article belongs to the American Institute of Aeronautics and Astronautics Inc, AIAA.
Keywords: Boundary layers; Expansion; Nozzle design; Nozzles; Propulsion; Sea level; Turbulence models, Code validation; Design optimization; Exact solution; Expansion angles; Expansion wave; Finite volume schemes; K-Omega turbulence model; Parametric study, Navier Stokes equations
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 16 Aug 2022 08:53
Last Modified: 16 Aug 2022 08:53
URI: https://eprints.iisc.ac.in/id/eprint/75753

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