A Numerical Investigation into Transonic Flight on Mars Utilizing a 2-D URANS Approach

Master thesis (2022)

Authors

M.S. Westheim Aerospace Engineering

Contributors

R. Schmehl Wind Energy - Aerospace Engineering (mentor)

F. Avallone Wind Energy - Aerospace Engineering (graduation committee member)

Theodorus Michelis Aerodynamics - Aerospace Engineering (graduation committee member)

M. Kotsonis Aerodynamics - Aerospace Engineering (graduation committee member)

Faculty

Aerospace Engineering, Aerospace Engineering

Mars CO2 Carbon dioxide Vortex shedding Transonic flow Compressibility Shock wave Shock wave boundary layer interaction Low Reynolds number High Mach number Laminar-turbulent transition Laminar Aerodynamic performance Naca0012

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Published Date

18-03-2022

Language

English

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Faculty

Aerospace Engineering

Abstract

Interest in powered flight on Mars has been growing in recent years, and as such new developments are being made in determining the effects the Martian atmosphere has on the flow physics and performance, specifically with regards to similarity parameters: the Reynolds number & the Mach number. This paper aimed to investigate whether the onset of transonic flight could result in decreased separation while improving aerodynamic performance due to the presence of a smeared shock. 2-D URANS simulations of a NACA-0012-34 airfoil were conducted with a SST k-w, y-intermittency model. The results find that an expansion fan delays separation, while the smeared shock weakens the adverse pressure gradient, similar to a shock control bump. The result is a minute increase in the lift-to-drag performance. The development of coherent structures within the separated shear-layer have also been seen to be impacted due to the stabilizing effect of compressibility on the Kelvin-Helmholtz instability.

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