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Lift test on propeller blade to determine which propeller would be the most efficient

Flow Analysis Over Alfa Romeo QV without any aerodynamic aids.

testing my seat for class
For Aerospace class

Trying to simulate wether the design will work making a mini jet engine irl

In this simulation, it is aimed to calculate the drag coefficient of an experimental rocket. Although the rocket geometry used is representative, the drag coefficient can be calculated for realistic models by following the simulation steps. K-w SST turbulence model was used for simulation. For the experimental rocket, the speed was taken 270 m / s and a ninety-degree (not realistic) flight angle assumption was made.

this project is dedicated to investigating the drag effect on a special type of aircraft's tail, in order to test its aerodynamic efficiency.

Simulation for a Solid-state propulsion drone

From Prandtl's 1933 paper on Bell lift distribution for minimizing the induced drag and recent works being published by NASA on PRANDTL D glider,  I decided to do a performance study and comparison of this type of lift distribution along with the conventional elliptic lift distribution,  that is to compare two wings with different lift distributions but with the same plan form area, taper ratio and aspect ratio

This project involves meshing externally a Boeing 777-200 LR Aircraft, and then simulating its' operation on flight facing an airflow with an axial velocity of 50 m/s.  It is one of the longest-range commercial airliners, with an exterior length and wingspan reaching 63.70 and 64.80 meters respectively.  For this case a model with removed engines was chosen in order to assist convergence and meshing. Also a Symmetry plane was added midst the Part, and half the part was used for meshing and simulation for simplification.  A steady state compressible flow simulation is executed to visualize the air flow around the bodywork and wings of the aircraft, as well as the pressure distribution while on flight.

This project  involves meshing a single-Shaft Turbofan Engine, and then simulating its' operation when facing an axial airflow of 150 m/s, while rotating with a velocity of 940 rad/sec (9000 rpm) . A Fan is used to bypass a large amount of air in the inside of the engine. For this case the typical Compressor, Combustion chamber and Turbine Stator were omitted, and only the Fan, Shaft, Shell and Turbine rotor were meshed and examined, in order to restrain the meshing requirements for complex, time consuming meshing and simulation.  A steady state incompressible flow simulation is executed to visualize the air flow through the components of the Turbofan, as well as the pressure and U magnitude distribution on the blades of the Fan and Turbine.

Link to  the extended compressible study (bigger domain included) : https://www.simscale.com/projects/fsite/turbofan_engine_extended_study/

Aerodynamic, Structural and Thermal analysis for the Quark-class Charm Amateur Rocket.
Instagram: @quarkproject
Gofundme: https://www.gofundme.com/f/quark-suborbital

Simulation of Max Q for F9 Rocket model. Project for University

Model by bjorn rudgley on GrabCAD:
https://grabcad.com/library/mxs-r-redbull-air-racer-1

3D model modified in order to be used in CFD.

This project demonstrates the static stress analysis of three aircraft engine bearing bracket models considering both linear and nonlinear material definition. The models used in this analysis are taken from GrabCAD users who were the winners of GrabCAD 'Airplane Bearing Bracket Challenge'. The models are tested with horizontal and vertical loading conditions as provided on the challenge page of GrabCAD.

This project involves the simulation of stress analysis of an aircraft wing. There are total 6 comparison configurations with 3 different models and two different load definition.

An aerodynamics study of the unique F-117 design in SimScale.

CFD analysis to verify the experimental results carried out on NACA 64015A Swpetback wing at AoA zero degree and Sweep angle 20 degrees.

Reference:  http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19980227185.pdf

The purpose of this project is to setup the wind tunnel conditions for external flows around objects at varying boundary conditions. Although X 43 is a hypersonic aircraft but for this project subsonic conditions are applied. 

A jet engine mount is analyzed regarding its harmonic response to the vibration of the jet engine.

Simulation of rocket engine with solid propellant as part of my PhD thesis.