&lt;/title&gt;&lt;/titles&gt; &lt;contributors&gt; &lt;person_name sequence='first' contributor_role='author'&gt; &lt;given_name&gt;VItaly&lt;/given_name&gt; &lt;surname&gt;DuDNIk&lt;/surname&gt; &lt;/person_name&gt; &lt;person_name sequence='additional' contributor_role='author'&gt; &lt;given_name&gt;GrIGory&lt;/given_name&gt; &lt;surname&gt;DuDNIk&lt;/surname&gt; &lt;/person_name&gt; &lt;person_name sequence='additional' contributor_role='author'&gt; &lt;given_name&gt;VIktor&lt;/given_name&gt; &lt;surnam

Stalewski, W.

doi:10.5604/05096669.1202204

Cited by 5 publications

(5 citation statements)

References 0 publications

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“…It is achieved 40 percent mass reduction in composite wing-box instead of Aluminum wing. Stalewski (2016Stalewski ( , 2017 proposed two alternative main rotors aerofoil for light gyroplanes. The first designed rotor were made of Aluminum alloy show that there is an increase in maximum speed of 10 percent and reduction in drag force is 7.5 percent, compared to NACA 9H12M.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The coordinates to develop the airfoil profile is given in Table 1. provided by NACA (Stivers and Rice, 1946;Stalewski, 2016).…”

Section: Fig 1 Naca 8-h-12 Airfoil Profilementioning

confidence: 99%

“…A gyroplane is a type of rotorcraft using an unpowered rotor operating by autorotation to develop lift. An enginepowered propeller to provide thrust which is necessary to balance the gyroplane drag force (Stalewski, 2016). Generally, a two-bladed teetering rotor is used in modern gyroplanes with simple design.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, they are lighter, more reliable and require less maintenance than helicopters (Trchalík, 2009). In contrast to helicopters, the torque of gyrocopter rotor does not come from an engine but from aerodynamic forces generated by airflow passing through the rotor disc (Trchalík, 2009;Simhachalam et al, 2015;Stalewski, 2016).…”

Section: Introductionmentioning

confidence: 99%

“…Optimization methods are very effective tools which are improves the performance of contemporarily designed and constructed aircraft. A fast development in computational methods and computer hardware is lead to expand the range of applications (Stalewski, 2016).…”

Section: Introductionmentioning

confidence: 99%

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Design of Composite Gyrocopter Main Rotor Blade Involving Rib and Spar Elements

Degu

Alebel

2019

EPPM-Journal

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Gyrocopter or gyroplane is a type of rotorcraft that uses an unpowered main rotor in free autorotation to develop lift. Gyrocopter rotor blades have smaller cord length and longer span compared to helicopters blades. National Advisory Committee for Aeronautics (NACA) 8-H-12 gyrocopter rotor blade profile, unsymmetrical airfoil sections were used for this research. An attempt has been made in this work to investigate the effect of ribs and spar elements in response to applied load. Three possible modeling alternatives were studied to predict the actual induced stress and deformation of the blade: Model I is by considering the blade shell part only, Model II is blade shell with 25 numbers of ribs and without the spar element and Model III is blade shell with 25 numbers of ribs and with spar element. The rotor blade was sized based on single seat open frame and high-wind-start gyrocopter. Structural static analysis has been carried out to evaluate the strength of composite rotor blade using ANSYS Workbench 15. The results show that among these three proposed models; Model III had registered minimum Von Mises stress and deformation. Also the result reveals that by considering ribs and spar element during analysis of gyrocopter blade is crucial because, it will help to know the actual induced stress and deformation. The predicted value of induced stress and deformation is closer to the actual values will help the designer not to overdesign the parts. Consequently, the main drawbacks related to overdesign increase in weight and cost will be minimized; thereby the product operational efficiency will be improved.

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Section: Literature Reviewmentioning

confidence: 99%

“…The coordinates to develop the airfoil profile is given in Table 1. provided by NACA (Stivers and Rice, 1946;Stalewski, 2016).…”

Section: Fig 1 Naca 8-h-12 Airfoil Profilementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Design of Composite Gyrocopter Main Rotor Blade Involving Rib and Spar Elements

Degu

Alebel

2019

EPPM-Journal

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Analysis of the impact of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Diamond DA-20 aircraft

Smykla¹,

Kopeć²,

Wolski³

2021

J. Phys.: Conf. Ser.

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One of the factors affecting the aerodynamics and performance of aircraft profiles are flaps. The work presents the influence of selected types of flaps on Diamond DA-20 properties. The aircraft aerodynamics is described in detail. Furthermore, the three types of steady flight are presented and the ways of calculating the basic performance of the airplane are taken into consideration. The techniques used to carry out the research are discussed, the conclusions are drawn and the final results are presented. The aim of this article was to analyse the influence of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Diamond DA-20 aircraft. The research focused on the aircraft in smooth configuration and with four types of trailing-edge wing flaps: pop-up, split flap, single-slotted flap and double-slotted flap in 15° and 45° positions.

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Analysis of the performance of a new type of rotorcraft

Witczak

Małek

2019

atest

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The article analyses the performance of the newly designed rotorcraft. A new concept for the equipment and use of rotorcraft for transport purposes was also presented. The work focuses on the use of gyroplanes for these purposes as a special type of rotorcraft with specific properties. The initial aircraft design developed and described includes structural assumptions, technological solutions, cabin / cargo ergonomics, economy and operational safety. Particular attention has been paid to rotorcraft equipment depending on which version it is to be configured to. The work also includes the design of the initial geometry of the rotorcraft. A solid showing the formulated assumptions that will be used for numerical analysis is presented. On its basis, an approximate analysis was made of the determination of basic performance and mass distribution depending on the equipment version. In addition, the method of numerical analysis of rotorcraft body and its results together with their development is presented. The results of numerical simulation were analyzed and conclusions regarding the correctness of gyroplanes for transport purposes were formulated.

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Cited by 5 publications

References 0 publications

Design of Composite Gyrocopter Main Rotor Blade Involving Rib and Spar Elements

Design of Composite Gyrocopter Main Rotor Blade Involving Rib and Spar Elements

Analysis of the impact of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Diamond DA-20 aircraft

Analysis of the performance of a new type of rotorcraft

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