Design of morphing wing with surface discontinuity

Tarnowski, Andrzej; Goetzendorf‐Grabowski, Tomasz

doi:10.1177/0954410018794317

Cited by 7 publications

(4 citation statements)

References 9 publications

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“…In recent years, a development of new methods of computational fluid dynamics (CFD) has enabled the simulation of many phenomena occurring during the flow of liquids around solid bodies. Proper configuration of specialized numerical codes allowed to analyze complex geometric surfaces or even morphing wings on early stages of the design process like showed in Goraj et al (2018) and Goetzendorf-Grabowski and Tarnowski (2018). Moreover, rapid development of more reliable tools for multiphysics calculations allowed the designers to address more problems at the very beginning or at early stages of the design process.…”

Section: Introductionmentioning

confidence: 99%

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Olejnik

Dziubiński

Kiszkowiak

2021

AEAT

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Purpose The purpose of this paper is to simulate with in-depth reconstruction of existing geometry a process of cooling of the aircraft engine in pusher configuration, which is more problematic than usually used, tractor configuration. Moreover, a complex thermal and fluid flow analysis is necessary to verify that an adequate cooling is ensured and that temperatures in the engine nacelle are maintained within the operating limits. Design/methodology/approach Methodology used in this research is based on computational fluid dynamics tools to model adequately the internal and the external flow, to find the state of cooling system and research the results of baffles modification inside the engine cover. Additionally, two types of the cover with different sizes of inlets and outlets are tested. Findings The results showed the influence of baffles modifications and changes in inlets and outlet sizes on the mass flow rate and temperature distributions inside the engine nacelle. The best configuration of air inlets and outlets was determined. Practical implications The method used in the research is the safest method in testing of such cases, provided the proper approach in modeling is taken. The collaboration of internal and external flow is crucial and should not be replaced with assumed flow rate through inlet and outlet area. The obtained results will help in future studies on cooling systems of engines in pusher configuration. Originality/value The work presents original results obtained by the authors during a complex fluid flow and heat transmission analysis and is a part of the design project of the OSA patrol aircraft.

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Section: Introductionmentioning

confidence: 99%

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Olejnik

Dziubiński

Kiszkowiak

2021

AEAT

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“…The UAV system “Baltic” was selected as the test platform, built in the weight class up to 25 kg, designed in the flying wing configuration (Figure 1). It is a continuation of the smaller UAV research project with similar geometry, which has been presented in earlier papers (Mieloszyk et al , 2020; Tarnowski et al , 2018). The geometry of the aircraft is the result of a unique numerical optimization framework developed by the authors, which incorporates full flight dynamic stability constraints.…”

Section: Introductionmentioning

confidence: 97%

Designing aerodynamic devices for UAV – lessons learned

Mieloszyk,

Tarnowski,

Goetzendorf-Grabowski

2023

AEAT

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Purpose Designing new aircraft that are state-of-the-art and beyond always requires the development of new technologies. This paper aims to present lessons learned while designing, building and testing new UAVs in the configuration of the flying wing. The UAV contains a number of aerodynamic devices that are not obvious solutions and use the latest manufacturing technology achievements, such as 3D printing. Design/methodology/approach The design solutions were applied on an airworthy aircraft and checked during test flights. The process was first conducted on the smaller UAV, and based on the test outcomes, improvements were made and then applied on the larger version of the UAV, where they were verified. Findings A number of practical findings were identified. For example, the use of 3D printing technology for manufacturing integrated pressure ports, investigation of the adverse yaw effect on the flying wing configuration and the effectiveness of winglet rudders in producing yawing moment. Practical implications All designed devices were tested in practice on the flying aircraft. It allowed for improved aircraft performance and handling characteristics. Several of the technologies used improved the speed and quality of aerodynamic device design and manufacturing, which also influences the reliability of the aircraft. Originality/value The paper presents how 3D printing technology can be utilized for manufacturing of aerodynamic devices. Specially developed techniques for control surface design, which can affect adverse yaw problem and aircraft handling characteristics, were described.

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“…In this paper, for the purpose of mass estimations methods evaluation, two UAV composite structures will be examined. The first one is a 5 kg UAV in the flying wing configuration (Tarnowski et al , 2018) shown in Figure 1. It has a composite structure made with composite wet layup vacuum technology.…”

Section: Introductionmentioning

confidence: 99%

Comparison of different fidelity mass analyses

Mieloszyk

Tarnowski

Goetzendorf‐Grabowski

et al. 2021

AEAT

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Purpose Aircraft structure mass estimation is a very important issue in aerospace. Multiple methods of different fidelity are available, which give results with varying accuracy. Sometimes these methods are giving a high discrepancy of estimated mass compared to the real mass of the structure. The discrepancy is especially noticeable in the case of small aircraft with a composite structure. Their mass properties highly depend not only on the material but also on technology and the human factor. Moreover, methods of mass estimation for unmanned aerial vehicle (UAV) platforms are even less established and examined. The purpose of this paper is to present and discuss various methods of mass estimation. Design/methodology/approach The paper presents different procedures of mass estimation for small UAVs with a composite structure. Beginning from the simplest one, where mass is estimated basing on a single equation and finishing with a mass estimation based on finite element method model and three-dimensional computer-aided design model. The results from all methods are compared with the airworthy aircraft and conclusions are discussed. Findings Mass of flying aircraft was estimated with different methods and compared. It revealed levels of accuracy of the investigated methods. Moreover, the influence on structure mass of human factor, glueing and painting is underlined. Practical implications Mass of the structure is a key factor in aerospace, which influences the performance of the aircraft. Thorough knowledge about the accuracy of the mass estimation methods and possible sources of discrepancies in mass analyses provides an essential tool for designers, which can be used with confidence and allows for the development of new cutting-edge constructions. Originality/value There are very few comparisons of mass estimation methods with an actual mass of manufactured and functional airframes. Additionally, mass estimation inaccuracies based on technological issues are presented, which is seldom done.

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Design of morphing wing with surface discontinuity

Cited by 7 publications

References 9 publications

CFD simulation of engine nacelle cooling on pusher configuration aircraft

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Designing aerodynamic devices for UAV – lessons learned

Comparison of different fidelity mass analyses

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