Designing a full-scale Surface Model of Bombardier Global 7500 Business Jet
Using the real-time dimensions available on the internet and provided 3 views of the aircraft, a 1:1 scale surface model is created using Catia v5.
Comparison of Theoretical and Numerical (NASTRAN) Structural Analysis of a Beam
A comparative study was carried out for fun to revise basic FEA concepts in NASTRAN. The displacement of a cantilever beam under a point load is calculated by hand and compared to numerical results performed using NASTRAN's beam library.
The hand calculation for the cantilever beam's displacement under a point load yielded 1.91×10^−5, closely matching the NASTRAN numerical result of 1.92×10^−5, with a negligible difference of 0.5%, validating the accuracy of both methods.
Structural Analysis of the fuselage floor for support optimization
3D modeling in CATIA software to visualize and design aircraft fuselage substructures, which are then validated for reliability using Ansys Structural tool to ensure the selection of a robust fuselage framework based on performance analysis.
Design and Integration of an RC Helicopter Main Rotor Assembly
Creating 45+ different mechanical parts and 4 sub-assemblies to integrate the whole main rotor assembly in Catia V5.
The helicopter rotor assembly is the main mechanism in helicopters to produce the lift. It has sub-assemblies like a swashplate, main rotor shaft housing, control links and main rotor holder.
The image below shows a static structural analysis of the main rotor blade in the Ansys Fluent module. Providing about 1 kg of lift, the blade undergoes maximum stress of 0.155 G Pascal at the hub which is within the safe limit for carbon fiber.
Aerodynamic Analysis of a VKI Turbine Blade
Analyzing a turbine blade to study the turbine performance using parameters like isentropic Mach number and inlet & outlet temperatures & pressures.
The images above indicate the 3D CFD domain of the geometry to be analyzed. The following images show the meshing (kept less dense as per project requirement) of the domain and derived CFD results of the Mach number, Pressure and Temperature.
The distribution of Isentropic Mach number over the blade surface is calculated by creating the number of planes perpendicular to the surface and taking the mass flow average value of the parameter on these particular planes. The images below shows the graphical representation of the distribution.
The pressure loss in the turbine cascade is calculated using this formula
CFD Analysis of an RS-25 rocket engine nozzle
Using the Ansys Fluent tool, a CD nozzle of the RS-25 aka Space Shuttle Main Engine was analyzed to study different operating conditions and the related behavior of Mach number, pressure and temperature.
The design of the nozzle using the original dimensions was carried out in Solidworks. The design is shown in the image below.
The following images show the meshing and the results of different operating conditions:
1. Subsonic Choke 2. Supersonic Design 3. Normal shock in the nozzle 4. Oblique shock 5. Prandtl- Mayer expansion.
When the back pressure at the nozzle exit lies somewhere between the oblique shock condition and expansion condition, when the exit flow points directly in the normal direction to the engine cross-section, it gives the optimum and efficient thrust making it the best operating condition.
Design and Analysis of a Bio-mimicked Turbine Blade
A comparative study of a conventional and bio-mimicked blade was carried out. The designs were created and modified using Solidworks and the aerodynamic analysis was performed using Ansys Fluent module.
For a bio-inspired blade to be more effective, the pitch angle must be greater than the critical value (36 Degrees).
When the pitch angle is more than critical, a bio-inspired blade performs more efficiently than a conventional blade.
Additionally, it is more effective and produces more lift as compared to conventional blades.
NACA 4-digit airfoil Analysis using Thin Airfoil Theory, Vortex Panel Method and Finite Wing Theory
The thin airfoil theory, vortex panel method and finite wing theory are used for the performance evaluation of the airfoils NACA 1408 and NACA 4424.
The performance evaluation is done using MATLAB and from the results, the lift coefficient is calculated over the different angles of attacks.
The motive is to check the variation in results from using different methods as well as to analyze them to predict the possibly accurate performance of an airfoil
Modeling of a 2-Feet wide Conveyor System in Solidworks and it's Motion Analysis
For practising purpose, modelled different parts of a conveyor system and assembles them to perform a motion-study incorporating elements like motor and gravitational force
Many More to be Published