School of Engineering Department of Mechanical and Aerospace Engineering 159 Aerodynamic Flow Study Supervisor: FU Lin / MAE Student: ARORA Arjun / AE Course: UROP 2100, Spring UROP 3200, Summer This study focuses on the understanding the aerodynamic performance of the ONERA M6 wing in a transonic flow along with the effectiveness of the turbulence model used by running a CFD simulation and validating it against experimental data found online. The case will be analysed by observing the pressure distribution across the surface of the wing. The wing will be analysed at an angle of attack of 3.06° and a Mach number of 0.84. Based on the results and the data analysis it was observed that the numerical results were predominantly agreeable with the experimental data. The results showed that the SST turbulence model was more agreeable with the experimental data, especially at regions of complex flow characteristics. Aerodynamic Flow Study Supervisor: FU Lin / MAE Student: CHEUNG Tsz Hong / AE Course: UROP 1100, Summer This computational fluid dynamics (CFD) research project on aerodynamic flow research will particularly focus on the simulation of oblique shock waves. Simulations are conducted using the open-source software SU2 to numerically solve the Euler equations, which are simplified from the Navier-Stokes equations by ignoring viscous effects of the fluids. The research aims to explore and replicate the oblique shock phenomenon, which occurs when a supersonic flow encounters a corner or wedge, leading to a sudden compression and changes in flow properties like pressure and Mach number. By simulating scenarios with varying wedge angles and comparing the results to analytical solutions, the researcher aims to gain a better understanding of the complex field of computational fluid dynamics. Aerodynamic Flow Study Supervisor: FU Lin / MAE Student: TSE Chak Wang / AE Course: UROP 1100, Fall Various freestream Mach speed over a range of subsonic to supersonic speed (1.2M) is used to demonstrate the shockwave development and its effect on lift and drag coefficients on a subsonic NACA-0012 airfoil using SU2 CFD software. As freestream Mach increases, formation of bow shock near the leading edge is observed, and normal shock over the upper airfoil shifted towards trailing edge and transitioned to oblique shocks. These shockwaves led to a noticeable drop in lift coefficient and a considerable sharp rise in drag coefficient as freestream Mach gets closer to sonic speed from transonic region. Lift to drag ratio decreased by 93.08% for NACA-0012 when comparing its peak value in subsonic region and supersonic region.
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