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The French company Parrot, which specializes in the design and development of drones, uses CAESES for the design of drone propellers. The reason Parrot's engineers, who are experts in the drone market, adopted CAESES is to speed up the design process and provide customers with even more suitable products. Here, we will introduce the benefits and applications of CAESES at Parrot. *For detailed information, you can view the related links. For more details, please download the PDF or feel free to contact us.*

At the Technical University of Darmstadt in Germany (Institute of Gas Turbines and Aerospace Propulsion), research was conducted on the automatic optimization of the volute of centrifugal compressors and vane diffusers. This project was carried out in collaboration with NUMECA, a German company, and Kompressorenbau Bannewitz GmbH (KBB), a turbo machinery manufacturer. CAESES was used for shape creation, while NUMECA's products were utilized for mesh model creation and CFD analysis. In CAESES, a parametric model was created that allowed for variations in the cross-sectional shape and area distribution of the volute. For the diffuser, a non-axisymmetric design was implemented, enabling quick shape transformations by varying the misalignment angle, blade twist, chord length, pitch, and rotation through a parametric model. *For more detailed information, please refer to the related links. You can download the PDF for more details or feel free to contact us.*

The turbo pump is an important component in the design of launch rockets for space using liquid fuel. It is a component that supplies the necessary fuel flow to achieve a large thrust while maintaining a high combustion chamber pressure, and it is used in rocket engine supply systems. Due to the need for high-precision performance predictions of turbo pumps for launch rockets, as well as designs based on these predictions, resulting from the significant reduction in total rocket engine weight, the very high rotational speed of the turbo pump, and the specifications of the pump in relation to the degree of depressurization in the liquid fuel storage tank, the goal is to maximize total reliability throughout the operational lifecycle. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

Centrifugal compressors are compact yet feature a high pressure ratio, and they are widely used in systems in the fields of aircraft and marine vessels. Impeller design is a crucial design aspect of centrifugal compressors and has a significant impact on compressor performance. In this case, we conducted automatic performance optimization using CAESES combined with CFD tools on an existing centrifugal compressor impeller model. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

The blades used in aircraft engines and gas turbines become very hot, so cooling air is supplied to the countless holes on the blade surface through cooling passages provided inside the blades. In conventional design methods, automatic optimization was considered difficult due to the complexity of shapes, robustness of mesh generation, and computation time. However, this case presents an example of fully automated optimization using CAESES. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

The research and development project VIT-VI focuses on artificial intelligence (AI) technology and its application in the development of virtual and sustainable aircraft engines. The emphasis is on building and enhancing AI capabilities, as well as increasing the use of artificial intelligence technology to improve productivity in data and simulation-driven design. CAESES offers the potential to automate the design investigation and optimization process of shapes in complex flows. *For more detailed information, please refer to the related link. You can download the PDF for more details or feel free to contact us.*

Using the general-purpose thermal fluid analysis software AICFD, we will conduct a performance analysis of the Rotor37 compressor. Rotor37 is a classic case of CFD compressible fluid calculations and is often used to verify the software's performance in the flow problem around the blades of a transonic axial compressor. We will analyze the three-dimensional flow characteristics of the compressor rotor, focusing on rotating machinery with practical engineering backgrounds derived from research results by NASA. *For more detailed information, please refer to the related links. For further inquiries, feel free to download the PDF or contact us directly.*

This article introduces the reliability analysis of solid fuel rockets using the general-purpose finite element analysis software AIFEM. The formulation, molding process, materials, and manufacturing processes of the rocket's solid fuel propellant directly affect the engine's performance. By using AIFEM to comprehensively evaluate the performance state throughout the entire lifecycle of the propellant column—from curing and cooling to transportation, storage, and discharge heating and cooling—we can achieve a comprehensive reliability assessment solution. *For more details, please refer to the related links. For further information, feel free to download the PDF or contact us.

Using the general-purpose finite element analysis software AIFEM, we will conduct topology optimization analysis of an aircraft engine turbine disk. Since a typical turbine disk is designed based on the engineer's experience, knowledge, and numerous tests, it can be time-consuming and costly, and it may be difficult to achieve an ideal design effect that breaks through existing design thinking. By utilizing AIFEM's topology optimization function, we will perform structural optimization of the turbine disk, taking into account the coupling of thermal loads and centrifugal forces, to obtain a better shape. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

Using the general-purpose thermal fluid analysis software AICFD, we will conduct a transonic analysis of the M6 wing. The M6 wing is a classical test case for studying transonic flow and is a semi-infinite airfoil designed by the French aerospace research institute ONERA. The M6 wing exhibits typical transonic airfoil characteristics, such as shock waves that appear on the wing under specific conditions and expansion waves behind the shock waves. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

Using the general-purpose data analysis and modeling software DTEmpower, we will conduct a data-driven strength evaluation of the reusable spacecraft wall structure. Reusable spacecraft are a crucial tool for enabling transportation between space and the ground, and the evaluation of the load-bearing capacity of wall structures, as typical load-bearing components, is significantly related to the overall safety performance of the spacecraft. However, traditional finite element methods often require over 100 minutes of computation time for a single buckling analysis of an enhanced cylindrical exterior, leading to high costs. *For more detailed information, please refer to the related links. For further inquiries, feel free to download the PDF or contact us.*

The descent rate of an aircraft during landing significantly exceeds the normal landing descent rate, resulting in excessive landing impact loads and a reduction in the strength margin of the landing gear and fuselage structure. Landing loads are related not only to mass but also to the pull from the rotor during the flight state at landing and the structure of the landing gear itself. Conventional methods for predicting aircraft landing loads require spending hours on dozens of simulations under operational conditions, making it impossible to quickly and accurately obtain design solutions that meet the requirements. *For more detailed information, please refer to the related link. For further details, you can download the PDF or feel free to contact us.*

Comprehensive engineering simulation software with unlimited licensing This article introduces CAA analysis of NACA airfoils using TCAE. This project focuses on the NACA 0012 airfoil BANCIIIc3 benchmark [1] (3D code: 0.4[m], span: 10%) and delves into the field of computational aeroacoustics (CAA). By adopting advanced techniques such as acoustic analogy and Ffowcs Williams-Hawkings, we explore unsteady simulations with a physical time of 1[s] through finite volume CFD simulations in a cell-centered framework. *For more detailed information, you can view it through the related links. For more details, please download the PDF or feel free to contact us.*

This article introduces the air intake optimization of ramjet engines using AIPOD, our self-developed optimization platform. Ramjet engines are designed for air intake at Mach numbers of 3 and above, where the mixture flows in and the exit becomes subsonic, making it a type of jet engine. To accommodate different flight Mach numbers, a center cone called a spike can be moved forward and backward, and when the maximum flight Mach number of 3.5 is reached, the Mach line formed at the tapered vertex intersects exactly with the lip. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.

Aircraft engine manufacturers are working daily on product development to meet the stringent demands of reducing exhaust emissions and fuel consumption. This effort requires further improvements in the design process to efficiently create aerodynamically superior compressor designs. In recent years, developing appropriate blade shapes that meet global design and performance requirements with high efficiency has necessitated numerous iterative calculations between different software tools for shape creation and fluid analysis. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*

The Wright brothers first flew over a century ago, but now we live in an era where we can fly efficiently and affordably to the far corners of the world. In the future, it is expected that supersonic and hypersonic flights exceeding Mach 5 at altitudes above 90,000 feet will allow travel from the UK to Australia in just four hours, and this remarkable achievement could be realized within 20 years. Even more impressive is the development of spaceplanes that bridge the realms of air and space. *For more details, please refer to the related links. For further information, you can download the PDF or feel free to contact us.*

UAVs are controlled by a wireless remote control device and an embedded program control device, and they are classified into various forms such as unmanned fixed-wing aircraft, unmanned vertical take-off and landing vehicles, unmanned airships, unmanned helicopters, and unmanned multi-rotor aircraft. Their applications are wide-ranging, including aerial photography, agriculture, disaster relief, infectious disease monitoring, mapping, journalism, and film and television production. For optimization, a fully parametric blade model targeting the wing shape of unmanned aerial vehicles is created, and by integrating automated design with CFD analysis, appropriate design proposals are identified. *For more detailed information, please refer to the related links. For further inquiries, feel free to download the PDF or contact us.*