Proper blade design, selection and use continue to gain importance with the developing technology, aviation and space industry. Many applications use wings such as aircraft (planes, helicopters, etc.), UAV (Unmanned Aerial Vehicle), wind turbines and so on. This study covers a NACA 0009 profiled wing with a 111 mm span and chord and its CFD analysis using Ansys version 15.0. Three-dimensional analysis has been done using Ansys Fluent. A geometry was created, this geometry was meshed properly, tighter especially close to the wings, and its analysis was completed using the k-w turbulence model. In total 2,078,272 nodes and 2,036,295 elements have been formed in the mesh. Four different angles of attack have been tested which are 0°, 5°, 10° and 15° at 37,000 Reynolds number. Generated mesh has an average skewness rate of 1.3 and an average orthogonal quality rate of 0.97. Velocity contours and streamlines have been compared to the literature. Lift and drag coefficients have been monitored. As the angle of attack increases, it is seen that shocks form at the trailing edge especially at 15° angle of attack and therefore aerodynamic performance of the NACA 0009 at different angles has been tested. With a L/D ratio of 10.03, the 5° angle of attack have been prevailed in comparisons.

In this study, a novel approach was employed to enhance the performance of a Bowman brand EC-2028 shell-and-tube heat exchanger (STHE) by introducing perforated plates. The heat exchanger was first tested in a real system within a laboratory environment to establish baseline performance data. Computational fluid dynamics (CFD) analysis revealed that flow velocities in the middle tubes were higher due to their alignment with the main flow direction, resulting in decreased heat transfer efficiency. To address this issue, a perforated plate with concentric circles was introduced at the cold fluid entry. This plate, devoid of central holes, featured circles with radii of 9, 18, 27, 36, 45, 54, and 63 mm, each containing 6, 10, 17, 24, 30, 36, and 42 equidistant holes, respectively. The introduction of the perforated plate led to a decrease of approximately 0.33°C in the hot outlet temperatures, indicating an improvement in heat transfer efficiency. To further enhance performance, various configurations were tested by progressively closing holes from the innermost to the outermost circles. Eight different configurations, including the control, were evaluated under counterflow conditions. The CFD model was validated with experimental data before introducing the perforated plates, ensuring the accuracy of the simulations. The findings demonstrated significant improvements in heat transfer efficiency, with the optimized perforated plate configurations leading to more uniform flow distribution and reduced pressure drops. This study's novel approach of using perforated plates to modulate flow and enhance thermal performance highlights a new avenue for optimizing STHE designs, contributing to more efficient thermal management solutions in industrial processes.

The increase in aerospace composites usage for structural components demands advanced repair analysis. Overlay repairs of carbon fiber-reinforced polymer laminates offer an alternative that is easier to perform and less time-consuming to produce than the widely used tapered scarf repair and stepped lap. Composite specimen manufacturing was based on both twill carbon/epoxy prepreg and wet lay-up. The repair was performed with both prepreg and wet extra plies to the parent prepreg structure. However, the design of overlay joints must be carefully investigated to avoid generating stress concentration regions at free edges. This study examined specific extra ply terminations' impact on peak stresses in the adhesive bond line. Linear finite element analysis was performed to conduct a maximum principal stress study with a focus on three joint design parameters: ply material, overply effect, and stacking sequence. FEA accurately predicted experimentally observed responses and provided further insight into the failure behavior of the structure. Results showed that overlay joints have a strong sensitivity to ply material type, the number of overply, and stacking sequence. The introduction of overplies provided protection and stiffness at joint tips, and an overply material behavior was identified. The location of 0̊ plies in the composite laminates was highlighted as an important factor. The analysis was then extended to three-dimensional FE models for verification. In conclusion, results showed that high-stress concentration in overlay joints can be mitigated with the introduction of overplies and appropriate changes in joint design parameters to reduce stress peaks at joint tips and corners.

Watermelon is among the most widely cultivated fruits globally, yet it suffers a high waste rate of 45% due to its short shelf life. In 2023, global watermelon production reached 99.7 million tons, with China and Türkiye contributing 60.1 million and 3.5 million tons, respectively. This study explores the potential of processing discarded watermelons into long‐lasting food ingredients to mitigate waste and enhance sustainability. Two test samples were developed: one combining watermelon pulp with flour, and another incorporating both watermelon pulp and rind with flour. The research also highlights the underutilized potential of watermelon rind as a valuable food ingredient. Experiments using a drum dryer produced ingredients with a moisture content of 3.40–3.77 g/100 g and water activity of 0.361–0.37, ensuring an extended shelf life. The new ingredients, rich in sugars and dietary fiber, offer a sustainable, natural alternative for industrial applications and can be produced 15.8%–19.1% cheaper than the value of their components. Redirecting 45% of global watermelon waste into food ingredients could potentially offset 2.7 million tons of CO2e emissions globally and 94,500 tons of CO2e in Türkiye annually. This study not only provides a sustainable solution to watermelon waste but also emphasizes efficient agricultural land use, reduced carbon emissions, minimized water consumption, and higher‐quality product development. By transforming a frequently discarded by‐product into valuable food ingredients, this research supports global sustainability efforts and promotes innovative approaches to reducing food waste.

In the study, the end mill made of titanium material and having a unique design with a 4-flute was simulated during the milling of the workpiece with a geometry of a rectangular prism made of aluminum material. Ansys Explicit Dynamics was used in the study. Modeling and simulation of the milling process were made with finite element analysis for the estimation of the strength properties. The end mill is chosen as a titanium alloy, while the milled workpiece is aluminum. All parameters were kept constant and only the depth of cut was examined in three scenarios 3, 6, and 9 mm. The simulations were carried out by taking the spindle speed of 4000 RPM and the feeding rate of 3350 mm/s. One of the conveniences provided by Explicit Dynamics is that it can be solved in very small time intervals, and for this reason, the time step in the analysis is solved by taking 0.001 seconds. While hexahedral mesh is applied to the tool, a tetrahedral mesh is applied to the workpiece. The generated mesh has 8,012 nodes and 17,052 mesh elements. Average deformations for both tool and workpiece are 36.92, 38.10, and 38.29 mm, respectively. Strain also shows a similar trend to the total deformation and the average values for all three scenarios were found to be 2.84 x 10-3, 4.43 x 10-3 and 3.99 x 10-3 mm/mm. Also, the stress values were obtained as 78.23, 76.83, and 77.99 MPa.

This study provides a comprehensive numerical investigation of altitude-dependent combustion performance and emissions of a commercial aircraft engine, leveraging real engine data to evaluate kerosene-fueled operation across six flight levels: FL300, FL318, FL336, FL354, FL372, and FL390. The combustion chamber geometry was modeled using Siemens NX, simplified in ANSYS SpaceClaim, and meshed with a five-layer inflation strategy to ensure proper boundary layer resolution. A high-quality mesh was achieved, and a mesh independence study was conducted to ensure numerical accuracy. Using the realizable k –ε turbulence model with enhanced wall treatment and an eddy-dissipation approach for turbulence-chemistry interactions, the results show that lower flight levels are associated with higher combustion efficiency, with peak temperatures exceeding 2500 K at FL300. Conversely, higher altitudes demonstrated reduced combustion efficiency and increased unburned fuel fractions, providing insights into the performance and environmental impact of altitude-dependent aircraft operations. These results may assist in optimizing engine design and operational strategies for improved fuel efficiency and reduced environmental impact across varying altitudes.